Embraer EMB145 Operation Manual Download

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AIRPLANE

OPERATIONS

MANUAL

CREW

AWARENESS

REVISION 38

2-04-30

Page

Code

M-145/1

114

STATIC ALERT/WARNING ENVELOPE

MODE 2A TERRAIN CLOSURE RATE

UPPER LIMIT BASED ON AIRSPEED

UPPER LIMIT (ft)=1650+8.9(AIRSPEED−220)

AIRSPEED EXPANSION AREA

AIRSPEED<220kt

AIRSPEED EXPANDS UPPER LIMIT

WHEN BETWEEN 220 AND 310 kt

ALERT/WARNING AREA

30 ft

1220 ft

200

400

600

800

1000

1200

1600

1800

2000

2200

2400

2600

2800

1400

2000

4000

6000

8000

MINIMUM TERRAIN CLEARANCE −ft

5733 ft/min AT 1650 ft,

2038 ft/min

3545 ft/min

CLOSURE RATE−ft/min

300 ft

TERRAIN
TERRAIN

PULL UP

WHOOP
WHOOP

10000

12000

9800 ft/min AT 2450 ft, AIRSPEED>310 kt

EM145AOM042035A.DGN

GPWS/EGPWS MODE 2A SCHEMATIC

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Summary of Contents for EMB145

Page 1: ...s export control laws and regulations Diversion contrary to the EAR and other laws and regulations is strictly forbidden The above restrictions may apply to data on all pages of this document Copyrigh...

Page 2: ...countries export control laws and regulations Diversion contrary to the EAR and other laws and regulations is strictly forbidden The above restrictions may apply to data on all pages of this document...

Page 3: ......

Page 4: ...structive suggestions on how we can further improve our documentation or service Your feedback will be acknowledged and we will advise you of the action we intend to take Sincerely Embraer Flight Oper...

Page 5: ...ge Code Date of Page Revision Name Position Company Fax Number Phone Number E Mail Comment Suggestion Space reserved for Embraer CCF n Comment received Date Acknowledged Person in Charge Action to be...

Page 6: ...ination of loose snow to dry snow 1 01 12 code 05 Included new block code containing information applicable to airplane Post Mod Service Bulletin 145 21 0050 1 01 30 code 03 Included information regar...

Page 7: ...ust Lock Caution Lights remain blinking until unlocking cycle is completed 1 02 79 code 01 Changed temperature reference for Engine Start during cold weather operations Included information about airp...

Page 8: ...in blinking until unlocking cycle is completed 2 14 15 code 02 Included new block code containing information applicable to airplane Post Mod SB 145 21 0031 SB 145 21 0033 and SB 145 21 0050 2 15 00 c...

Page 9: ...NS MANUAL Page 4 Code 105 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 2 16 15 code 01 Included information related to the incorporation of SB 145 35 0008 which provides g...

Page 10: ...IRPLANE OPERATIONS MANUAL RECORD OF TEMPORARY REVISIONS TEMPORARY REVISION 41 1 RTR 1 Copyright by Embraer Refertocoverpagefor details RECORD OF TEMPORARY REVISIONS AOM 145 1114 105 TR 41 1 SEP 15 201...

Page 11: ...RECORD OF TEMPORARY REVISIONS AIRPLANE OPERATIONS MANUAL RTR 2 TEMPORARY REVISION 41 1 Copyright by Embraer Refertocoverpagefor details INTENTIONALLY BLANK...

Page 12: ...N 12 JUN 01 1999 REVISION 13 SEP 20 1999 REVISION 14 DEC 15 1999 REVISION 15 APR 28 2000 REVISION 16 SEP 29 2000 REVISION 17 MAR 30 2001 REVISION 18 JUN 29 2001 REVISION 19 AUG 24 2001 REVISION 20 OCT...

Page 13: ...Page 2 Code 105 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 REVISION 40 NOV 14 2013 REVISION 41 MAR 06 2015 NOTE The references to the deleted pages from the previous rev...

Page 14: ...ON 41 1 LEP 7 105 REVISION 41 1 LEP 8 105 REVISION 41 1 LEP 9 105 REVISION 41 1 LEP 10 105 REVISION 41 1 LEP 11 105 REVISION 41 1 LEP 12 105 REVISION 41 1 LEP 13 105 REVISION 41 1 LEP 14 105 REVISION...

Page 15: ...105 REVISION 41 1 LEP 42 105 REVISION 41 1 TOC 1 01 REVISION 25 ALL 1 TOC 2 01 REVISION 23 1 00 00 1 01 REVISION 39 ALL 1 00 00 2 01 REVISION 39 1 00 00 3 01 REVISION 40 1 00 00 4 01 REVISION 39 1 00...

Page 16: ...01 REVISION 41 1 00 30 4 01 REVISION 41 1 00 30 5 01 REVISION 41 1 00 30 6 01 REVISION 41 1 00 30 7 01 REVISION 41 1 00 30 8 01 REVISION 41 1 00 30 9 01 REVISION 41 1 00 30 10 01 REVISION 41 1 00 35 1...

Page 17: ...ISION 31 1 01 05 5 21 REVISION 31 1 01 05 6 21 REVISION 31 1 01 10 1 01 REVISION 41 FAA 1 01 10 2 01 REVISION 41 1 01 10 3 01 REVISION 41 1 01 10 4 01 REVISION 41 1 01 10 5 01 REVISION 41 1 01 10 6 01...

Page 18: ...01 52 3 01 SEP 20 1999 1 01 52 4 01 SEP 20 1999 1 01 56 1 02 REVISION 29 FAA AHRS 1 01 56 2 02 REVISION 29 1 01 56 3 02 REVISION 29 1 01 56 4 02 REVISION 25 1 01 56 1 07 REVISION 29 FAA AHRS IRS 1 01...

Page 19: ...REVISION 41 ALL 1 02 01 2 01 REVISION 41 1 02 05 1 01 REVISION 41 ALL 1 02 05 2 01 REVISION 41 1 02 05 3 01 REVISION 41 1 02 05 4 01 REVISION 41 1 02 09 1 01 REVISION 41 ALL 1 02 09 2 01 REVISION 41...

Page 20: ...ION 37 1 02 17 6 02 REVISION 37 1 02 17 7 02 REVISION 37 1 02 17 8 02 REVISION 37 1 02 17 9 02 REVISION 37 1 02 17 10 02 REVISION 37 1 02 17 11 02 REVISION 40 1 02 17 12 02 REVISION 40 1 02 17 13 02 R...

Page 21: ...2 57 3 02 REVISION 36 1 02 57 4 02 REVISION 36 1 02 61 1 01 REVISION 37 ALL 1 02 61 2 01 REVISION 37 1 02 69 1 01 REVISION 39 ALL 1 02 69 2 01 REVISION 39 1 02 73 1 01 REVISION 37 ALL 1 02 73 2 01 REV...

Page 22: ...SION 41 1 02 79 20 01 REVISION 41 1 02 79 21 01 REVISION 41 1 02 79 22 01 REVISION 41 1 02 79 23 01 REVISION 41 1 02 79 24 01 REVISION 41 1 02 79 25 01 REVISION 41 1 02 79 26 01 REVISION 41 1 02 79 27...

Page 23: ...ISION 40 1 02 80 22 01 REVISION 40 1 02 80 23 01 REVISION 40 1 02 80 24 01 REVISION 40 1 02 80 25 01 REVISION 40 1 02 80 26 01 REVISION 40 1 02 80 1 02 REVISION 36 ANAC FAA UNS 1K FMS 1 02 80 2 02 REV...

Page 24: ...02 81 4 01 REVISION 17 1 02 81 5 01 MAR 30 2001 1 02 81 6 01 MAR 30 2001 1 02 82 1 01 REVISION 28 ALL 1 02 82 2 01 REVISION 28 1 02 83 1 02 REVISION 38 ANAC FAA 1 02 83 2 02 REVISION 38 1 02 83 3 02 R...

Page 25: ...SION 36 1 02 95 12 05 REVISION 36 1 02 95 13 05 REVISION 36 1 02 95 14 05 REVISION 36 1 02 95 15 05 REVISION 36 1 02 95 16 05 REVISION 36 1 02 95 17 05 REVISION 36 1 02 95 18 05 REVISION 36 1 02 95 19...

Page 26: ...1 03 11 3 03 REVISION 40 1 03 11 4 03 REVISION 40 1 03 11 5 03 REVISION 40 1 03 11 6 03 REVISION 40 1 03 11 7 03 REVISION 40 1 03 11 8 03 REVISION 40 1 03 14 1 03 REVISION 29 FAA 1 03 14 2 03 REVISIO...

Page 27: ...EVISION 38 1 03 37 4 03 REVISION 38 1 03 37 5 03 REVISION 40 1 03 37 6 03 REVISION 38 1 03 38 1 03 OCT 02 2001 FAA 1 03 38 2 03 MAR 30 2001 1 03 39 1 03 REVISION 40 FAA 1 03 39 2 03 REVISION 40 1 03 4...

Page 28: ...48 5 03 REVISION 40 1 03 48 6 03 REVISION 36 1 03 50 1 03 REVISION 40 FAA 1 03 50 2 03 REVISION 39 1 03 50 3 03 REVISION 39 1 03 50 4 03 REVISION 40 1 03 50 5 03 REVISION 39 1 03 50 6 03 REVISION 40...

Page 29: ...03 REVISION 40 1 03 57 6 03 REVISION 40 1 03 57 7 03 REVISION 40 1 03 57 8 03 REVISION 40 1 03 58 1 03 DEC 20 2002 FAA 1 03 58 2 03 MAR 30 2001 1 03 59 1 03 REVISION 40 FAA 1 03 59 2 03 REVISION 37 1...

Page 30: ...3 03 REVISION 37 1 03 70 4 03 REVISION 40 1 03 70 5 03 REVISION 38 1 03 70 6 03 REVISION 38 1 03 70 7 03 REVISION 38 1 03 70 8 03 REVISION 37 1 03 70 9 03 REVISION 38 1 03 70 10 03 REVISION 38 1 03 70...

Page 31: ...SION 38 1 03 70 38 03 REVISION 38 1 03 70 39 03 REVISION 38 1 03 70 40 03 REVISION 38 1 03 70 41 03 REVISION 38 1 03 70 42 03 REVISION 38 1 03 70 43 03 REVISION 38 1 03 70 44 03 REVISION 38 1 03 70 45...

Page 32: ...EVISION 27 1 04 10 4 01 REVISION 27 1 04 10 5 01 REVISION 27 1 04 10 6 01 REVISION 27 1 04 10 7 01 REVISION 27 1 04 10 8 01 REVISION 27 1 04 10 9 01 REVISION 27 1 04 10 10 01 REVISION 27 1 04 10 11 01...

Page 33: ...REVISION 28 1 04 15 12 02 REVISION 28 1 04 15 13 02 REVISION 28 1 04 15 14 02 REVISION 28 1 04 15 15 02 REVISION 28 1 04 15 16 02 REVISION 28 1 04 15 17 02 REVISION 28 1 04 15 18 02 REVISION 28 1 04...

Page 34: ...3 02 REVISION 39 1 04 25 4 02 REVISION 36 1 04 30 1 02 REVISION 41 135 145 FAA lb 1 04 30 2 02 REVISION 41 1 04 30 3 02 REVISION 41 1 04 30 4 02 REVISION 41 1 04 30 5 02 REVISION 41 1 04 30 6 02 REVIS...

Page 35: ...02 REVISION 41 1 04 30 34 02 REVISION 41 1 04 30 35 02 REVISION 41 1 04 30 36 02 REVISION 41 1 04 30 37 02 REVISION 41 1 04 30 38 02 REVISION 41 1 04 30 39 02 REVISION 41 1 04 30 40 02 REVISION 41 1 0...

Page 36: ...N 40 145 A1 and A1P lb 1 05 05 2 02 REVISION 40 1 05 05 3 02 REVISION 40 1 05 05 4 02 REVISION 40 1 05 05 5 02 REVISION 40 1 05 05 6 02 REVISION 40 1 05 05 7 02 REVISION 40 1 05 05 8 02 REVISION 40 1...

Page 37: ...VISION 40 1 05 10 18 02 REVISION 40 1 05 10 19 02 REVISION 40 1 05 10 20 02 REVISION 40 1 05 10 21 02 REVISION 40 1 05 10 22 02 REVISION 40 1 05 15 1 02 REVISION 40 145 A1 and A1P lb 1 05 15 2 02 REVI...

Page 38: ...5 25 3 02 REVISION 40 1 05 25 4 02 REVISION 40 1 05 25 5 02 REVISION 40 1 05 25 6 02 REVISION 40 1 05 25 7 02 REVISION 40 1 05 25 8 02 REVISION 40 1 05 30 1 03 REVISION 40 145 A1 and A1P FAA 1 05 30 2...

Page 39: ...VISION 39 1 05 35 14 02 REVISION 39 1 05 35 15 02 REVISION 39 1 05 35 16 02 REVISION 39 1 05 35 17 02 REVISION 39 1 05 35 18 02 REVISION 39 1 05 35 19 02 REVISION 39 1 05 35 20 02 REVISION 39 1 05 35...

Page 40: ...39 145 A1 FAA lb 1 05 45 2 06 REVISION 39 1 05 45 3 06 REVISION 39 1 05 45 4 06 REVISION 39 1 05 45 5 06 REVISION 39 1 05 45 6 06 REVISION 39 1 05 45 7 06 REVISION 39 1 05 45 8 06 REVISION 39 1 05 50...

Page 41: ...06 10 3 01 SEP 20 1999 1 06 10 4 01 SEP 20 1999 1 06 15 1 02 REVISION 37 lb 1 06 15 2 02 REVISION 37 1 06 15 3 02 REVISION 37 1 06 15 4 02 REVISION 37 1 06 15 5 02 REVISION 37 1 06 15 6 02 REVISION 37...

Page 42: ...VISION 29 1 06 40 6 03 REVISION 29 1 06 40 7 03 REVISION 29 1 06 40 8 03 REVISION 29 1 06 40 9 03 REVISION 29 1 06 40 10 03 REVISION 29 1 06 40 11 03 REVISION 29 1 06 40 12 03 REVISION 29 1 06 40 13 0...

Page 43: ...ISION 38 145 Interior 3 1 07 30 2 43 REVISION 38 1 07 30 1 44 REVISION 37 145 Interior 4 1 07 30 2 44 REVISION 37 1 07 30 1 45 REVISION 38 145 Interior 5 1 07 30 2 45 REVISION 38 1 07 30 1 46 REVISION...

Page 44: ...30 2 74 REVISION 31 1 07 30 1 75 REVISION 36 145 Configuration 6A 1 07 30 2 75 REVISION 38 1 07 30 1 76 REVISION 39 145 Configuration 7 1 07 30 2 76 REVISION 38 1 07 30 1 79 REVISION 36 145 Configura...

Page 45: ...002 1 07 80 8 01 DEC 20 2002 1 07 90 1 01 REVISION 30 ALL 1 07 90 2 01 REVISION 30 1 07 90 3 01 REVISION 30 1 07 90 4 01 REVISION 30 1 07 95 1 01 REVISION 39 135 140 145 1 07 95 2 01 REVISION 39 1 08...

Page 46: ...REVISION 40 1 08 33 6 01 REVISION 40 1 08 33 7 01 REVISION 40 1 08 33 8 01 REVISION 40 1 08 49 1 01 REVISION 27 ALL 1 08 49 2 01 REVISION 27 1 08 52 1 01 REVISION 27 ALL 1 08 52 2 01 REVISION 27 1 08...

Page 47: ...00 145 Interior 1 50 pax 1 10 08 2 01 SEP 29 2000 1 10 08 1 02 SEP 29 2000 145 Interior 2 50 pax 1 10 08 2 02 SEP 29 2000 1 10 08 1 03 SEP 29 2000 145 Interior 3 50 pax 1 10 08 2 03 SEP 29 2000 1 10 0...

Page 48: ...Interior Option 2A 1 10 08 2 23 REVISION 34 1 10 10 1 01 REVISION 13 ALL 1 10 10 2 01 REVISION 31 1 10 15 1 01 DEC 20 2002 ALL 1 10 15 2 01 DEC 20 2002 1 10 15 3 01 DEC 20 2002 1 10 15 4 01 DEC 20 20...

Page 49: ...1 11 40 3 03 REVISION 19 1 11 40 4 03 REVISION 35 1 11 40 5 03 REVISION 19 1 11 40 6 03 REVISION 29 1 11 40 7 03 AUG 24 2001 1 11 40 8 03 SEP 20 1999 1 11 40 9 03 REVISION 31 1 11 40 10 03 REVISION 30...

Page 50: ...10 10 01 REVISION 39 1 12 10 11 01 REVISION 39 1 12 10 12 01 REVISION 39 1 12 15 1 01 REVISION 30 ALL 1 12 15 2 01 REVISION 23 1 12 15 3 01 APR 28 2000 1 12 15 4 01 APR 28 2000 1 12 20 1 01 REVISION...

Page 51: ...REVISION 38 1 12 25 16 04 REVISION 38 1 12 25 17 04 REVISION 38 1 12 25 18 04 REVISION 38 1 12 25 19 04 REVISION 38 1 12 25 20 04 REVISION 38 1 12 30 1 01 REVISION 38 ALL 1 12 30 2 01 REVISION 37 1 12...

Page 52: ...12 60 9 01 REVISION 41 1 12 60 10 01 REVISION 41 1 12 60 11 01 REVISION 41 1 12 60 12 01 REVISION 41 1 12 60 13 01 REVISION 41 1 12 60 14 01 REVISION 41 1 12 60 15 01 REVISION 41 1 12 60 16 01 REVISI...

Page 53: ...LIST OF EFFECTIVE PAGES AIRPLANE OPERATIONS MANUAL 1 LEP Page 42 Code 105 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 54: ...N AND DEFINITION OF TERMS 1 01 LIMITATIONS 1 02 NORMAL PROCEDURES 1 03 EMERGENCY AND ABNORMAL PROCEDURES 1 04 PERFORMANCE 1 05 FLIGHT PLANNING 1 06 WEIGHT AND BALANCE 1 07 LOADING 1 08 CONFIGURATION D...

Page 55: ...TABLE OF CONTENTS AIRPLANE OPERATIONS MANUAL 1 TOC Page 2 Code 01 REVISION 23 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 56: ...00 Page 1 Code 01 AOM 145 1114 SECTION 1 00 GENERAL INFORMATION AND DEFINITION OF TERMS TABLE OF CONTENTS Page Block General Information 1 00 00 Definition of Terms 1 00 10 Units Conversion 1 00 20 EI...

Page 57: ...has complete and accurate information on any modifications made to the delivered configuration Any modifications improvements add ons or any other changes made to the airplane without the involvement...

Page 58: ...ety Agency is identified as both EASA and JAA Therefore whenever you find either it corresponds to European certification This is because since September 28 2003 EASA took over responsibility for the...

Page 59: ...factors errors are minimized Some operational requirements just define the main subjects that must be presented in an Airplane Operations Manual matter However even detailing the Airplane Operations M...

Page 60: ...rator with the help of EMBRAER operations software runway analysis driftdown and route analysis AIRPLANE OPERATIONS MANUAL STRUCTURE The EMBRAER Airplane Operations Manual is organized in two volumes...

Page 61: ...ght Controls 2 14 Pneumatics Air Conditioning and Pressurization 2 15 Ice and Rain Protection 2 16 Oxygen 2 17 Flight Instruments 2 18 Navigation and Communication 2 19 Autopilot Each of the above sec...

Page 62: ...pplicable Some codes may be applicable to more than one configuration whilst more than one code may be specific to one configuration As an example there could be Block Codes Number of pages Numbering...

Page 63: ...es to the text A vertical line adjacent to the page number indicates relocated or rearranged text or illustrations The basic issuance date of this Manual is presented in the title page The revisions a...

Page 64: ...NING OPERATING PROCEDURES TECHNIQUES AND OTHER RELATED INFORMATION WHICH MAY RESULT IN PERSONAL INJURY OR LOSS OF LIFE IF NOT CAREFULLY FOLLOWED CAUTION OPERATING PROCEDURES TECHNIQUES AND OTHER RELAT...

Page 65: ...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 kph Kilograms per Hour kt Knot lb Pounds m Meter m...

Page 66: ...AFS Autoflight System AGL Above Ground Level AHC Attitude and Heading Computer AHRS Attitude and Heading Reference System AIL Aileron ALC APU Line Contactor ALT Altitude ALTN Alternate AM Amplitude M...

Page 67: ...ic Takeoff Thrust Control System AUTO Automatic AUX Auxiliary AVAIL Available AWU Aural Warning Unit B B C Back Course BACV Bleed Air Check Valve BAGG Baggage BATT Battery BBC Backup Battery Contactor...

Page 68: ...el Data Link CDH Clearance Delivery Head CDL Configuration Deviation List CCW Counterclockwise CG Center of Gravity CIS Cabin Interphone System CL Climb CLB Climb CLR Clear CLSD Closed CMC Central Mai...

Page 69: ...ion Height DISC Disconnect DME Distance Measurement Equipment DMU Data Management Unit DN Down E EADI Electronic Attitude Director Indicator EBC Essential Bus Contactor EBV Engine Bleed Valve ECM Elec...

Page 70: ...tter EMG EMERG Emergency EMER PILOT Emergency Pilot ENG Engine ERR Error ESU Electronic Sequence Unit ET Elapsed Time EXT External EXTG Extinguish F FADEC Full Authority Digital Electronic Control FCO...

Page 71: ...Brake FU Fuel Used FVS Flap Velocity Sensor FWD Forward G G S GS Glide Slope GCU Generator Control Unit GI Ground Idle GLC Generator Line Contactor GMAP Ground Mapping GMT Greenwich Mean Time GND Gro...

Page 72: ...n ICU Integrated Communication Unit Interphone Control Unit IFR Instrument Flight Rules IFOG Interferometer Fiber Optic Gyros ILS Instrument Landing System IM Integrated Computer Configuration Module...

Page 73: ...Engine Inoperative LGEU Landing Gear Electronic Unit LH Left hand LOC Localizer LOGO Logotype LP Low Pressure LRN Long Range LSB Lower Sideband LSS Lightning Sensor System LX Lightning Detection M M...

Page 74: ...ng Weight MRW Maximum Design Ramp Weight MSU Mode Select Unit MTOW Maximum Design Takeoff Weight MZFW Maximum Design Zero Fuel Weight N N1 Fan Speed N2 High Pressure Rotor Shaft Speed NAV Navigation N...

Page 75: ...ss PRESS Pressure PRV Pressurizing Valve PSU Passenger Service Unit PTT Press To Transmit Q QFE Question Field Elevation Field Elevation Pressure Q code QNE Question Normal Elevation Standard Pressure...

Page 76: ...Static Air Temperature SBC Shed Bus Contactor SCV Starting Control Valve SELCAL Selective Call SL Sea Level SLVD Slaved SOV Shutoff Valve SPC Stall Protection Computer SPS Stall Protection System SQ S...

Page 77: ...erage U U S NAS U S National Airspace System V V Volt V1 Decision Speed V2 Takeoff Safety Speed VA Volt Ampere VAPP VOR Approach Mode VA Design Maneuvering Speed VEF Critical Engine Failure Speed VFE...

Page 78: ...MS MEANING VMCG Ground Minimum Control Speed VMO Maximum Operating Speed VOR VHF Omnidirectional Range VR Rotation Speed VREF Landing Reference Speed VREFXX Landing Reference Speed associated to the f...

Page 79: ...by Embraer Refertocoverpagefor details AOM 145 1114 SYMBOLS AND NOTATIONS SYMBOL MEANING OR SHUTOFF VALVE PRIORITY VALVE CHECK VALVE RESTRICTOR RELIEF VALVE OPTIONAL EQUIPMENT SYSTEM MODULE COMMUNICA...

Page 80: ...ercury in Hg Millibar mb 33 8636 Kilogram kg Pounds lb 2 2046 Kilogram force per Square meter kgf m 2 Pound per Square Inch psi 0 0014 Kilometer km Nautical Mile nm 0 5396 Kilometer per hour km h Knot...

Page 81: ...GENERAL AIRPLANE OPERATIONS MANUAL 1 00 20 Page 2 Code 01 REVISION 13 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 82: ...on EICAS 14 it was green up to 90 psi and amber above it Higher brake temperature limits for LR brakes ICE SPS ADVANCED renamed SPS ICE SPEEDS Flaps 18 capability Autopilot wing rocking improvements V...

Page 83: ...iguration module IM 600 of each IC 600 The configuration module stores several aircraft configuration parameters VERSION 16 5 Anti Icing system improvements new messages and logic A I LOW CAPACITY inc...

Page 84: ...on stored in the IM 600 135 or 145 Engine Type Long Range Fuel Tank or English Metric Units CONFIG MISMATCH is still active in case of discrepancy of the other parameters that do not trigger the CHK I...

Page 85: ...und the upper limit of the green band is 115 psi In all other thrust ratings it is 95 psi 2 For EICAS version 17 with FADEC B 5 1 1 the amber band upper limit is 155 psi 3 For N2 88 the amber band bet...

Page 86: ...pe mode is cancelled Inhibition of VERTICAL MODE OFF message if the FD mode is cancelled by changing the preselected altitude Inhibition of VERTICAL MODE OFF and or LATERAL MODE OFF messages if a late...

Page 87: ...indication should be 0 V Flap System Flap 22 indication in red on EICAS display and NO TAKEOFF CONFIG message when the aircraft is not certified to take off with flaps 22 Fuel System New Message FUEL...

Page 88: ...l E1 2 FPMU NO DISP only applicable to EMB 145 XR model E1 2 EXCEEDANCE A1E thrust rating modes included on EICAS RMU MFD New upper range limit for fuel flow indication due to A1E engine ITT and N2 Dy...

Page 89: ...sage changed from caution to advisory only applicable to airplanes properly equipped for High Altitude Operation Navigation System The Radio Altimeter indication was modified in order to reduce the di...

Page 90: ...case the Autopilot reverts to basic mode and automatically couples to the co pilot Flight Director as expected If a vertical mode is selected to either climbing or descending following the Symbol Gene...

Page 91: ...value shall be displayed again on the HGS combiner There will be no modifications on the HGS system Ice Protection ICE COND A ICE INOP message logic change in the previous logic under ice condition on...

Page 92: ...145 23 0003 Introduces VHF Channel Spacing of 8 33 KHz SB 145 23 0028 Incorporates Aural Alert For CMU Message SB 145 25 0261 Baggage Compartment Liner Reinforcement SB 145 25 0287 Installs Cut Out A...

Page 93: ...s Modifications to Extend the Speed Envelope of the EMB 145XR Model SB 145 31 0040 Configures the EMB 145XR Model for CAT II Operation SB 145 31 0042 Incorporates EICAS 20 5 Version SB 145 31 0051 Rep...

Page 94: ...egulator Valve SB 145 49 0010 Improves the Airborne Auxiliary Power APU SB 145 49 0012 Changes Auxiliary Power Unit APU Electronic Sequence Unit ESU feeder bus SB 145 49 0014 Replaces the APU Air Inle...

Page 95: ...AE3007A1 3 Engines SB 145 73 0025 Incorporates FADEC B7 6 Version on AE3007A3 Engines SB 145 73 0026 Incorporates FADEC B7 6 Version on AE3007A1E Engines SB 145 73 0027 Incorporates FADEC B8 0 Versio...

Page 96: ...Limitations 1 01 10 Supplementary Operational Limitations 1 01 12 Systems Crew Alerting 1 01 30 Electrical 1 01 32 Fuel 1 01 36 APU 1 01 38 Powerplant 1 01 40 Pressurization 1 01 48 Ice and Rain Prot...

Page 97: ...d Airplane Flight Manual Flight crewmembers should have all limitations committed to memory except tables and charts Some items may not be included herein as they may be identified in a panel placard...

Page 98: ...uired by airworthiness and operating regulations are approved installed and in an operable condition Visual VFR Instrument IFR Icing conditions MAXIMUM NUMBER OF SEATS NON AFM The maximum number of av...

Page 99: ...LIMITATIONS AIRPLANE OPERATIONS MANUAL 1 01 01 Page 2 Code 01 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 100: ...Max Ramp Weight MRW Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 45635 lb 45414 lb 41226 lb 37698 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 4600...

Page 101: ...Max Ramp Weight MRW Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 45635 lb 45414 lb 41226 lb 38250 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 4600...

Page 102: ...eight MRW Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 45635 lb 45414 lb 41226 lb 37698 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 0 1...

Page 103: ...GHT Max Ramp Weight MRW Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 45635 lb 45414 lb 41226 lb 38250 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 4...

Page 104: ...imited 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...

Page 105: ...LIMITATIONS EMB 145 ER FAA AIRPLANE OPERATIONS MANUAL 1 01 05 Page 6 Code 07 REVISION 31 INTENTIONALLY BLANK...

Page 106: ...MRW Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 48722 lb 48501 lb 42549 lb 39462 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 520...

Page 107: ...off Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 50044 lb 49823 lb 43651 lb 40564 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 52000 0 5 10 15...

Page 108: ...ght MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 48722 lb 48501 lb 42549 lb 39462 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 52000 0 5 10 15 20 25...

Page 109: ...keoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 50044 lb 49823 lb 43651 lb 40564 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 52000 54000 0...

Page 110: ...imited 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...

Page 111: ...LIMITATIONS EMB 145 LR FAA AIRPLANE OPERATIONS MANUAL 1 01 05 Page 6 Code 08 REVISION 31 INTENTIONALLY BLANK...

Page 112: ...OW Max Landing Weight MLW Max Zero Fuel Weight MZFW 46495 lb 46275 lb 42549 lb 39462 lb 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 52000 54000 0 10 20 30...

Page 113: ...Weight MRW Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 46495 lb 46275 lb 42549 lb 39462 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50...

Page 114: ...able determined from Takeoff Distance on Contaminated Runway and Accelerate Stop Distance on Contaminated Runway charts Maximum takeoff weight as limited by brake energy and determined from Maximum Ta...

Page 115: ...LIMITATIONS EMB 145 MP FAA AIRPLANE OPERATIONS MANUAL 1 01 05 Page 4 Code 20 REVISION 26 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 116: ...ight MRW Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 46495 lb 46275 lb 41226 lb 37698 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 5000...

Page 117: ...ight MRW Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 46495 lb 46275 lb 41226 lb 38250 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 5000...

Page 118: ...Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 46495 lb 46275 lb 41226 lb 37698 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 0 10 20...

Page 119: ...mp Weight MRW Max Takeoff Weight MTOW Max Landing Weight MLW Max Zero Fuel Weight MZFW 46495 lb 46275 lb 41226 lb 38250 lb 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000...

Page 120: ...able determined from Takeoff Distance on Contaminated Runway and Accelerate Stop Distance on Contaminated Runway charts Maximum takeoff weight as limited by brake energy and determined from Maximum Ta...

Page 121: ...LIMITATIONS EMB 145 EP FAA AIRPLANE OPERATIONS MANUAL 1 01 05 Page 6 Code 21 REVISION 31 INTENTIONALLY BLANK...

Page 122: ...0 40 30 20 10 0 10 20 30 40 50 60 ALTITUDE ft STATIC AIR TEMPERATURE C ISA 35 C TAKEOFF LANDING 37000 ft 21 5 C 1000 ft 52 C 54 C 8000 ft 65 C 40 C 145CTA47 08OCT98 NOTE In the event of a landing belo...

Page 123: ...LIMITATIONS FAA AIRPLANE OPERATIONS MANUAL 1 01 10 Page 2 Code 01 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 124: ...an be safely extended VLE is the maximum speed at which the airplane can be safely flown with the landing gear extended and locked MANEUVERING SPEED VA VA 200 KIAS NOTE Maneuvers that involve angle of...

Page 125: ...ATING SPEED APPLICABLE TO ALL MODELS EXCEPT EMB 145 XR MODEL POST MOD SB 145 31 0038 0 5000 10000 15000 20000 25000 30000 35000 40000 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350 AL...

Page 126: ...XR MODEL POST MOD SB 145 31 0038 OR WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED 0 5000 10000 15000 20000 25000 30000 35000 40000 200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 3...

Page 127: ...Flaps 45 160 KIAS Above 10000 ft with Yaw Damper disengaged Flaps 22 180 KIAS Flaps 45 145 KIAS ELECTROMECHANICAL GUST LOCK Each time electromechanical gust lock lever is set to unlocked FREE position...

Page 128: ...n in flight depressurization is 10000 ft MSL unless MEA or otherwise required Maximum altitude for dispatch for an unpressurized flight is 10000 ft TURBULENT AIR PENETRATION SPEED AFM PROCEDURES At or...

Page 129: ...rpagefor details AOM 145 1114 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...

Page 130: ...FACTORY INCORPORATED 5000 0 5000 10000 15000 20000 25000 30000 35000 40000 70 60 50 40 30 20 10 0 10 20 30 40 50 60 ALTITUDE ft c STATIC AIR TEMPERATURE C ISA 35 C TAKEOFF LANDING c 37000 ft 21 5 C 10...

Page 131: ...LIMITATIONS ANAC FAA AIRPLANE OPERATIONS MANUAL 1 01 12 Page 2 Code 03 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 132: ...ATED 5000 0 5000 10000 15000 20000 25000 30000 35000 40000 70 60 50 40 30 20 10 0 10 20 30 40 50 60 ALTITUDE ft STATIC AIR TEMPERATURE C ISA 35 C 145XRFAA100 30JUN2003 TAKEOFF LANDING 37000 ft 21 5 C...

Page 133: ...LIMITATIONS FAA AIRPLANE OPERATIONS MANUAL 1 01 12 Page 2 Code 05 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 134: ...lgorithms prior version 213 213 currently do not account for man made obstacles Pilots should inhibit the Terrain Awareness Alerting and Display function by pressing the TERRAIN SYS OVRD button when w...

Page 135: ...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 aga...

Page 136: ...ONS MANUAL LIMITATIONS SEPTEMBER 20 1999 1 01 32 Page 1 Code 01 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...

Page 137: ...LIMITATIONS AIRPLANE OPERATIONS MANUAL 1 01 32 Page 2 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 138: ...been determined for an adopted fuel density of 6 767 lb US Gal When performing pressure refueling the usable fuel quantity in each tank may be reduced by 7 9 US Gal maximum FUEL SPECIFICATION Brazilia...

Page 139: ...LIMITATIONS AIRPLANE OPERATIONS MANUAL 1 01 36 Page 2 Code 03 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 140: ...n determined for an adopted fuel density of 6 767 lb US Gal When performing pressure refueling the usable fuel quantity in each tank may be reduced by 13 2 US Gal maximum FUEL SPECIFICATION Brazilian...

Page 141: ...LIMITATIONS AIRPLANE OPERATIONS MANUAL 1 01 36 Page 2 Code 04 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 142: ...nds 2 For airplanes Post Mod SB 145 49 0010 or equipped with an equivalent modification factory incorporated In this case the minimum temperature for APU start is 54 C up to 30000 ft 3 Minimum battery...

Page 143: ...LIMITATIONS AIRPLANE OPERATIONS MANUAL 1 01 38 Page 2 Code 02 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 144: ...AMETER 1 MIN MAX N1 100 N2 102 4 2 3 ITT START 800 C TAKEOFF MODES 948 C 4 CONTINUOUS 901 C OIL PRESSURE BELOW 88 N2 34 psi 95 psi 5 6 110 psi 5 7 AT OR ABOVE 88 N2 50 psi 8 95 psi 6 7 110 psi 7 OIL T...

Page 145: ...5 psi in all operational modes time limited to 2 minutes Total time above 110 psi may not exceed 5 minutes 8 While this is an abnormal condition operation between 50 psi and 34 psi is permitted during...

Page 146: ...es equipped with FADEC versions previous than B8 0 At least once a week a Thrust Assurance Check must be performed by selecting maximum takeoff mode during takeoff and checking engine parameters The T...

Page 147: ...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 21 C or for airplanes Pre Mod Rolls Royce SB AE3007A 79 025...

Page 148: ...IONS SEPTEMBER 20 1999 1 01 48 Page 1 Code 01 PNEUMATIC AIR CONDITIONING AND PRESSURIZATION PRESSURIZATION Maximum differential pressure 7 8 psi Maximum differential overpressure 8 1 psi Maximum diffe...

Page 149: ...LIMITATIONS AIRPLANE OPERATIONS MANUAL 1 01 48 Page 2 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 150: ...s 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 10 C or below when operating on ramps taxi ways...

Page 151: ...LIMITATIONS AIRPLANE OPERATIONS MANUAL 1 01 50 Page 2 Code 02 REVISION 24 WINDSHIELD WIPER OPERATION Maximum Airspeed for Windshield Wiper Operation 170 KIAS...

Page 152: ...se tables are based on FAA ADVISORY CIRCULAR 120 38 The tables show altitude limitations calculated for constant ozone concentration cabin stabilized at 8000 ft and both recirculation fans turned on F...

Page 153: ...0 330 320 320 340 75 N 330 330 330 320 320 340 70 N 350 330 330 330 320 340 65 N 360 340 330 330 340 330 330 330 330 340 350 60 N 360 350 340 340 330 330 340 330 350 350 55 N 360 350 350 340 340 340 3...

Page 154: ...10 300 290 270 270 270 310 290 55 N 340 310 330 300 310 300 290 290 290 290 310 300 50 N 350 320 350 310 320 310 270 290 290 290 310 320 45 N 350 330 320 320 320 320 290 310 310 310 330 330 40 N 340 3...

Page 155: ...LIMITATIONS AIRPLANE OPERATIONS MANUAL 1 01 52 Page 4 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 156: ...itude and heading information presented on PFD is valid For the AH 900 AHRS version the following limits are applicable Maximum latitude for alignment 78 15 Northern and Southern AHRS alignment will c...

Page 157: ...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 f...

Page 158: ...Track Angle Rate parameter AUTOPILOT APPLICABLE TO ALL MODELS EXCEPT EMB 145 XR The following limitations are applicable to the Autopilot For airplanes Pre Mod SB 145 31 0016 the use of the Autopilot...

Page 159: ...Engagement Height After Takeoff 500 ft Minimum Use Height 160 ft Malfunction altitude loss Cruise 80 ft Maneuver 40 ft ILS Approach 35 ft Descent below Minimum Decision Altitude on a non precision ap...

Page 160: ...itude and heading information presented on PFD is valid For the AH 900 AHRS version the following limits are applicable Maximum latitude for alignment 78 15 Northern and Southern AHRS alignment will c...

Page 161: ...n 60 S and 82 S Between 118 30 E and 160 E South of 82 S Between 0 and 180 W E NOTE Within the magnetic polar cut out regions AHRS heading data is not available INERTIAL REFERENCE SYSTEM Maximum latit...

Page 162: ...4 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 flo...

Page 163: ...able to transmit the Track Angle Rate parameter AUTOPILOT The following limitations are applicable to the Autopilot For airplanes Pre Mod SB 145 31 0016 the use of the Autopilot below 1500 ft AGL is o...

Page 164: ...neywell software version NZ4 8 or NZ5 2 must be installed FMS instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the FMS navi...

Page 165: ...tside the Brazilian Airspace with GPS as the navigation sensor ILS LOC LOC BC LDA SDF and MLS approaches using the FMS for guidance are prohibited When flying to an airport where GPS non overlay is th...

Page 166: ...ration with Autopilot coupled the pilot must use the Flight Guidance Controller for vertical control Advisory vertical guidance is available only in descent During oceanic North Atlantic NAT Minimum N...

Page 167: ...junction with Honeywell Off Line RAIM prediction program For single FMS installation in accordance with AC 20 130A along routes requiring a single Long Range Navigation LRN System provided it is recei...

Page 168: ...with dual Inertial Reference Systems IRS as installed has been found to comply with the requirements of FAA Order 8400 12A as amended as a primary means of navigation for flights up to 6 2 hours afte...

Page 169: ...ciated on the PFD The flight director is coupled to the LNAV mode GPS only approaches NOTE AC 90 94 deals with the use of GPS in the US National Airspace System NAS and in oceanic areas The general ap...

Page 170: ...roach mode and GPS integrity monitoring when using GPS for approach guidance must be available at the Final Approach Fix as indicated to the pilot by the INTEG amber annunciator being off and APP annu...

Page 171: ...en flying to an airport where GPS non overlay is the intended approach prior to dispatch the flight crew is required to verify that the predictive RAIM at the destination ETA is within the approach cr...

Page 172: ...route and terminal area operation with DR annunciated on the PFD the flight crew must verify the FMS position using VOR DME raw data or other appropriate means The airplane must have other navigation...

Page 173: ...RN System sensor on these routes Enroute and Terminal In accordance with AC 20 130A and TSO C129a B1 provided it is receiving usable signals from One VOR DME or multiple DME s GPS Instrument Approach...

Page 174: ...other crewmember Positive identification of the person wishing to enter the flight deck must be obtained before opening the door The security cockpit door must be kept closed and locked at all times d...

Page 175: ...LIMITATIONS AIRPLANE OPERATIONS MANUAL 1 01 70 Page 2 Code 01 REVISION 25 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 176: ...Yaw Damper System 1 Autopilot not required for EMB 135 and EMB 145XR models 2 Flight Director Systems 2 Primary Flight Displays PFD Windshield Wipers 2 VHF NAV Systems 1 VHF COMM System Both Engines C...

Page 177: ...evel Minimum Use Height MUH 50 ft Runway Visual Range RVR 1200 ft Maximum Tailwind except for EMB 145XR model 10 kt Maximum Crosswind except for EMB 145XR model 25 kt Maximum Tailwind EMB 145XR model...

Page 178: ...ual Range RVR 180 m WIND COMPONENTS For Low Visibility Takeoff operations the following wind components must not be exceeded Headwind 25 kt Tailwind 10 kt Crosswind 15 kt For AIII mode operations the...

Page 179: ...fertocoverpagefordetails AOM 145 1114 AIRPLANE EQUIPMENT LIMITATIONS AIRPLANE SUN VISOR With the HGS Combiner deployed airplane sun visors must not be placed in a position during takeoff approach or l...

Page 180: ...IRS NOTE IRS 1 must be operative in case of dual IRS installation 2 Air Data Computers ADC 3 VHF NAV Systems 2 Integrated Computers IC 2 Attitude and Heading Reference System AHRS NOTE AHRS is not app...

Page 181: ...Heading Reference System AHRS NOTE AHRS is not applicable in case of dual IRS installation Windshield Wipers NOTE For airplanes Pre Mod SB 145 30 0055 and Post Mod SB 145 30 0054 or with an equivalent...

Page 182: ...xternal Safety Inspection 1 02 05 Internal Safety Inspection 1 02 09 Power Up 1 02 13 Before Start First Flight 1 02 17 Before Start Through Flight 1 02 21 Engine Start 1 02 23 After Start 1 02 29 Bef...

Page 183: ...on Recovery 1 02 80 Traffic and Collision Avoidance 1 02 80 Transponder 1 02 80 RNP Approach 1 02 80 Performance Based Navigation PBN 1 02 80 Engine Engine Start with Airplane Batteries and Low Pressu...

Page 184: ...the event that any of the procedures are missing or unusable operations may be continued provided the approved AFM is available for use The normal procedures established are based on the assumption th...

Page 185: ...NORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 02 00 Page 4 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 186: ...RIFY POS Alternate Gear Extension Compartment CKD POWER UP Batteries 1 2 AUTO Avionics Master 1 or 2 PUSHED IN Batteries Voltage CKD Backup Battery EMB XR only CKD GPU Voltage if available CKD Avionic...

Page 187: ...Gust Lock UNLOCKED AFTER TAKEOFF Landing Gear UP FLAPS 0 Thrust Rating CLB Windshield Heating AS RQRD AIR COND PNEUM Panel SET Altimeters SET X CKD Pressurization CKD APU AS RQRD DESCENT Windshield H...

Page 188: ...ned airframe components etc Make sure that the airplane has the chocks and safety pins on as required If not advise the ground staff immediately The External Safety Inspection must be carried out prio...

Page 189: ...UNLOCKED position Ground Locking Pin REMOVED Static Discharger CONDITION Check that the static discharger touches the ground Landing and Taxi Lights CONDITION Hydraulic Compartment right side NO LEAK...

Page 190: ...freefall lever to reposition the uplock to the UNLOCKED position Gear Struts Wheelwells CONDITION NO LEAKS Ground Locking Pins REMOVED Brake Wear Indicators CHECK Wear indicators should be no less tha...

Page 191: ...NORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 02 05 Page 4 Code 01 REVISION 41 Copyright byEmbraer Refertocoverpagefordetails AOM 145 1114 INTENTIONALLY BLANK...

Page 192: ...the event that APU or GPU are not available batteries may be used NOTE Using batteries for an extended period will discharge them Maintenance Status CHECK Cockpit Emergency Equipment CHECKED Check for...

Page 193: ...be set to OVRD to operate the recirculation fans when the electrical system is energized by the APU generator AC Power IN Back up IN Avionics Master 1 2 OUT Emergency Lights OFF Fire Extinguishing Han...

Page 194: ...gen ON Make sure that the Shutoff Regulator Valve is in the ON position Passenger Oxygen AUTO Gust Lock LOCKED CAUTION NEVER MOVE CONTROL SURFACES SUCH AS FLAPS AND SPOILERS WITHOUT FIRST MAKING SURE...

Page 195: ...aware that once the airplane is energized if the handle is lifted from the detent the flaps will move to the commanded position Free Fall Lever Compartment CHECKED The OVERRIDE switch must be in the...

Page 196: ...uccessful APU start or if BATT 1 OFF BUS followed by APU GEN OFF BUS messages are displayed on EICAS the APU master switch must be set to OFF position and time intervals as stated above shall be obser...

Page 197: ...ry 1 to AUTO The minimum time for battery recharging is 30 minutes For cold soak operation refer to Operation in Icing Conditions section Once the batteries are on the pilot must concentrate on starti...

Page 198: ...ion Avionics Master 1 2 ON Switch the avionics master to ON Verify APU voltage and amperage on electrical page Amperage may be greater than 400 A APU GEN OVLD may appear on the EICAS at first while th...

Page 199: ...to climatize the airplane Both Packs ON XBLEED to OPEN Set both temperature controls to AUTO If control of the Pack 2 by the cabin attendant is desired select the corresponding knob to ATTD Recircula...

Page 200: ...battery 1 to AUTO While GPU is ON batteries will not be recharged The minimum time for battery recharging is 30 minutes For cold soak operation refer to Operation In Icing Conditions section GPU Volta...

Page 201: ...the EICAS at first while the APU recharge the batteries Do not bring any additional load on line until amperage is below 400 A Allow a few seconds for the APU GEN OVLD message to disappear before swi...

Page 202: ...below 24 V report to the maintenance personnel or recharge the affected battery by using the generators In case of recharging it is recommended that battery 1 be turned OFF before GPU disconnection A...

Page 203: ...NORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 02 13 Page 8 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 204: ...n board Data such as runway analyses driftdown analyses if applicable enroute diversion data etc must also be on board Make sure that documents which are legally required to be on board are really on...

Page 205: ...xygen flowing must be heard momentarily on the speaker thereby assuring the microphone electrical integrity Set the mask to 100 After finishing the test select the BOOM position on the Audio Panel App...

Page 206: ...also if the source of electrical power is the APU If the source is a GPU then set the selector to AUTO The AC PWR BACKUP and AVIONICS MASTER buttons are pressed Emergency Lights ARMED Switch the EMER...

Page 207: ...the following EICAS messages Warning APU FIRE ENG 1 2 FIRE BAGG SMOKE Caution APU FIREDET FAIL E1 2 FIREDET FAIL Fire Extinguisher handles illuminated BAGG EXTG button illuminated Aural fire warning...

Page 208: ...C knob to select the takeoff mode Press the STORE button one more time and the white mark will move to the REF TO TEMP line Use the DEC INC knob again to select the reference local temperature Each mo...

Page 209: ...ydraulic pumps to AUTO Verify that the indicated pressures are within 2900 r 200 psi Check also the hydraulic fluid level of systems 1 and 2 are within normal range Switch both electric hydraulic pump...

Page 210: ...ECKED Check on the MFD ECS page if the minimum pressure for flight crew is 1500 psi for three occupants or 1100 psi for two occupants For airplanes equipped with gaseous passenger oxygen system check...

Page 211: ...AP to his side and engage it verifying the AP and YD indications on the PFD Press the AP PUSHER TRIM button on the control wheel and verify the disengagement of the AP and the disappearance of the res...

Page 212: ...es selected according to the intended departure procedure showing the same magnetic heading flag free and with the heading bug set to the intended runway heading NOTE In case of heading split check if...

Page 213: ...t be guarded and not illuminated and QUICK DISCONNECT BUTTON must be released Carry out the Stall Protection System test as follows Pull the control column all the way back and momentarily press the S...

Page 214: ...on including the check if the DATABANK is still valid check for correct date and time and check for possible messages related to the status of the FMS Also if the flight plan needs to be entered it ca...

Page 215: ...weather terrain MSA noise abatement procedures low visibility procedures inoperative airplane components runway in use condition return alternate airports NOTAMs and any required operational procedure...

Page 216: ...n board Data such as runway analyses driftdown analyses if applicable enroute diversion data etc must also be on board Make sure that documents which are legally required to be on board are really on...

Page 217: ...xygen flowing must be heard momentarily on the speaker thereby assuring the microphone electrical integrity Set the mask to 100 After finishing the test select the BOOM position on the Audio Panel App...

Page 218: ...also if the source of electrical power is the APU If the source is a GPU then set the selector to AUTO The AC PWR BACKUP and AVIONICS MASTER buttons are pressed Emergency Lights ARMED Switch the EMER...

Page 219: ...t least 2 seconds the Fire Detection Test button while observing the following EICAS messages Warning APU FIRE ENG 1 2 FIRE BAGG SMOKE Caution APU FIREDET FAIL E1 2 FIREDET FAIL Fire Extinguisher hand...

Page 220: ...t is prompting for the selection of takeoff mode Use the DEC INC knob to select the takeoff mode Press the STORE button one more time and the white mark will move to the REF TO TEMP line Use the DEC I...

Page 221: ...c pumps to AUTO Verify that the indicated pressures are within 2900 r 200 psi Check also the hydraulic fluid level of systems 1 and 2 are within normal range Switch both electric hydraulic pumps to ON...

Page 222: ...displayed Following the simbology may be stowed or may be cleared if not desired during any remaining pre flight or taxi out Crew Passenger Oxygen Pressure CHECKED Check on the MFD ECS page if the mi...

Page 223: ...gnment NOTE The IRS knob should never be moved to ATT on ground If for any reason it is set to ATT restart the alignment process from scratch by setting the knob to OFF then back to NAV Flight Guidanc...

Page 224: ...runway heading Once these actions are complete the pilots must carry out an instrument crosscheck as follows Both AIRSPEED TAPES not showing speed EADI s level and flag free Both ALTIMETERS with thei...

Page 225: ...ain altitude tapes Check no ALT or SPD flags displayed MFD SYS Pages CHECK RMU SET The PF assigned for the flight must set the COMM and NAV frequencies as appropriate for the expected SID or departure...

Page 226: ...rd The test takes about 5 seconds and is valid if the amber light on the TEST button extinguishes Press the caution and warning light buttons to turn them off Trims CHECKED Verify that the aileron rud...

Page 227: ...table and already supplying power to the systems GPU is disconnected HGS Control Panel if installed SET Verification of the proper operation of all HCP displays can be accomplished by performing na HC...

Page 228: ...y in use condition return alternate airports NOTAMs and any required operational procedures that differ from the normal procedures It is recommended to perform the takeoff briefing before engine start...

Page 229: ...MANUAL 1 02 17 Page 14 Code 02 REVISION 37 AOM 145 1114 Safety Pins ON BOARD Verify that the safety pins are on board behind the CPT seat Locking Pins if applicable ON BOARD Verify that the locking p...

Page 230: ...T O page on the MFD Press the STORE button once and verify the white mark besides T O MODE which means that it is prompting for the selection of takeoff mode Use the DEC INC knob to select the takeoff...

Page 231: ...pressure for passenger system is 1150 psi This oxygen pressure must be enough for the intended flight Carry out the test as described in the Before Start First Flight procedures Flight Number and Cloc...

Page 232: ...rement is a reminder that the selected altitude has not been authorized by ATC yet Standby Instruments SET Set the QNH or QFE on the standby altimeter RMU SET The PF assigned for the flight must selec...

Page 233: ...n should be performed only after the airplane is energized by its generators APU and or engines provided that airplanes buses are stable and already supplying power to the systems GPU is disconnected...

Page 234: ...iefing should describe the departure procedures taxi out routes power reductions weather terrain MSA noise abatement procedures low visibility procedures inoperative airplane components runway in use...

Page 235: ...AGE pressing the trigger on the yoke and observe STEERING INOP message on EICAS No push back required or after push back ENGAGE pressing STEERING HANDWELL and observe STEERING INOP message disappear o...

Page 236: ...round personal clearance according to local authority allowances For engine start using APU or LPU refer to AOM section 1 2 81 Start Stop Selector START THEN RUN Turn the start selector to RUN for 2 s...

Page 237: ...ance according to local authority allowances For engine start using APU or LPU refer to AOM section 1 2 81 Start Stop Selector START THEN RUN Turn the start selector to RUN for 2 seconds then turn the...

Page 238: ...izes at about 64 N2 and 24 N1 Verify ITT fuel flow and oil pressure for normal indications CAUTION ABORT THE ENGINE START BY SELECTING THE START STOP SELECTOR TO STOP IF AN ABNORMAL ENGINE START IS DE...

Page 239: ...cal System SET If the SHED BUSES are set to OVRD switch them to AUTO APU AS REQUIRED Set the APU ON or OFF according to the electrical and pressurization systems The APU usage shall be defined for a s...

Page 240: ...CROSSBLEED ALT T O Open Closed Auto T O 1 Closed Open Open No icing E T O Closed Open Open ALT T O Open Closed Auto T O Open Closed Auto Icing E T O Open Closed Auto Takeoff Data CHECKED Check the ATT...

Page 241: ...rease N2 above 83 the engine oil temperature must be at 40 C minimum If the oil temperature is below 40 C after 4 minutes the engine should be run an additional 4 minutes before advancing the Thrust L...

Page 242: ...ction 1 02 79 Crossfeed OFF PC Power System if installed OFF The PC Power System must be turned off until the airplane reaches 10000 ft Lights ON Brakes Temperature CHECKED Verify on the MFD HYD page...

Page 243: ...should be once again applied Each time electromechanical gust lock lever is set to unlocked FREE position elevator movement must be checked This check must be performed at least 10 seconds after posit...

Page 244: ...t reported that the cabin is ready for departure NOTE If the ENGINE has not been running in the previous 90 minutes Cold Engine ensure at least 4 minutes to warm up before apply takeoff power If the E...

Page 245: ...Transponder TA RA Verify that the TCAS is set to ABOVE and that a proper range has been selected He must also check that the transponder code is the correct one and is set to TA RA Gust Lock UNLOCKED...

Page 246: ...NORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL INTENTIONALLY BLANK AOM 145 1114 1 02 37 Page 2 Code 01 REVISION 40...

Page 247: ...ange is not recommended According to engine vibration limits the pilot may elect not to reduce TLA for vibration below 2 5 IPS time limited to 5 minutes If vibration returns to the green range within...

Page 248: ...ON 30 At level off height altitude For takeoff with flaps 9 At V2 15 KIAS or higher FLAPS UP For takeoff with flaps 18 At V2 10 KIAS or higher FLAPS 9 At V2 30 KIAS or higher FLAPS UP For takeoff with...

Page 249: ...ds landing gear up after PF has requested and confirms the three white UP indications on the EICAS FLAPS 0 PNF retracts FLAPS at acceleration altitude according Normal takeoff for Flaps 9 18 or 22 sch...

Page 250: ...e transition altitude the altimeters are set to QNE by the respective pilots if it is an operation in ICAO airspace Pressurization CHECKED Once the air conditioning system is set verify that the press...

Page 251: ...the HCP the glideslope angle for the landing runway Select the desired mode Speed Bugs SET Check on the FMS the expected landing weight and set VREF VAPP VAPP CLB VFS on the MFD VAPP VREF wind correct...

Page 252: ...ollowing lights must be turned ON upon crossing 10000 ft LDG1 NOSE AND LDG2 During night time the LOGO light must also be turned ON Fasten Belts ON Switch the FASTEN BELTS light upon crossing 10000 ft...

Page 253: ...fore the outbound segment should be flown using any other mode Both pilots must verify that the frequencies and courses that were selected are correct for the intended approach Ensure that both PFD s...

Page 254: ...0 Up 180 200 180 200 9 Up Dn 160 18 22 Up Dn 140 150 45 Dn 140 Maximum Structural Landing Weight as specified on Limitations Section ONLY APPLICABLE TO EMB 145XR MODEL FLAP MANEUVERING SPEED KIAS BELO...

Page 255: ...speed VFE 160 KIAS requires maintenance action The maximum flap 22 and 18 extended speed VFE of 200 KIAS must not be exceeded in any condition However if momentary deviations happen to speeds up to 21...

Page 256: ...gear lever to the up position Minimum Airspeed APPROACH CLIMB SPEED Maintain the pitch as commanded by the Flight Director or pitch 10 if Go Around is being performed on raw data to maintain the airp...

Page 257: ...eck the three green lights before this item is confirmed Speed Brake CLOSE Flaps ___ SET Check that the flap position is the intended one for landing Landing Lights AS REQUIRED Auto Pilot Yaw Damper O...

Page 258: ...NORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 02 61 Page 2 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 259: ...all flight phases Air Conditioning and Pneumatic System AS REQUIRED Pressurization CHECK External Lights SET Turn ON the taxi light that must remain ON throughout the taxi regardless of the time of th...

Page 260: ...ocedures is recommended Transponder STBY Set the Transponder and the TCAS to Standby Gust Lock LOCKED The GUST LOCK must be applied immediately after the airplane leaves the runway NOTE In case of an...

Page 261: ...chocks are ON NOTE To avoid hydraulic fluid transference from system 1 to system 2 first apply brakes using the pedals and after pull the emergency parking brake handle To release the emergency parkin...

Page 262: ...ut down concurrently with the starting of the APU A minimum one minute interval between those two procedures is recommended NOTE If the overcurrent protection is actuated the airplane will enter in el...

Page 263: ...parked and the parking brake is applied the copilot must switch both electric hydraulic pumps to OFF Ice Protection System OFF Air Conditioning SET If passengers are to be disembarked through means o...

Page 264: ...NORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 02 73 Page 4 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 265: ...ternal Lights OFF Make sure that all internal and external lights are switched OFF with the exception of the cockpit dome light at night before switching OFF GPU or APU Passenger Signs Panel OFF Set E...

Page 266: ...it helps extending APU life If a GPU is the source of electrical power switch it OFF through the GPU button on the Electrical System panel Never leave the airplane unattended and energized A member o...

Page 267: ...e batteries are switched OFF Otherwise the emergency lights will illuminate and drain their batteries External Internal Lights OFF Make sure that all internal and external lights are switched OFF with...

Page 268: ...n the APU Shutting down the APU while bleed air is coming out of it helps extending APU life If a GPU is the source of electrical power switch it OFF through the GPU button on the Electrical System pa...

Page 269: ...must be OFF during takeoff and landing If fuel imbalance is verified Attitude WINGS LEVELED If left wing presents lower level Crossfeed Selector LOW1 If right wing presents lower level Crossfeed Selec...

Page 270: ...SUPPLEMENTARY PROCEDURES FUEL AIRPLANE OPERATIONS MANUAL 1 02 78 Page 2 Code 01 REVISION 33 INTENTIONALLY BLANK...

Page 271: ...n inspection to ensure that there is no ice accretion Do not touch the surfaces with bare hands as the skin may stick to a freezing surface Even at intermediate stops an external walk around is necess...

Page 272: ...ot permitted on the lower upper surface of the horizontal stabilizer or the upper surface of the wing Pitot Tubes TAT Static Ports and AOA Vanes CLEAR OF ICE Engine APU Air Inlet CLEAR OF ICE OR SNOW...

Page 273: ...U using external electrical power is 54 C 65 F If APU cannot be started apply heat from a ground cart directly into the APU compartment Do not allow the hot air from the ground heating cart to exceed...

Page 274: ...l Display may not be readable at temperature below 20 C Electric Hydraulic Pumps ON Check hydraulic pressure If pressure does not rise to normal values warm up the hydraulic reservoir compartment with...

Page 275: ...engine start In cold weather conditions the usage of dual ignition ignition switch rotated to the ON position is highly recommended for the first engine start of the day or if the engine has not been...

Page 276: ...lable for anti icing Moving thrust levers forward will cause the message to disappear On airplanes Pre Mod SB 145 30 0028 when Ice Detector Override Knob is at ENG on the ground TAT heating is on TAT...

Page 277: ...APU AIR INLET Parking Brake ON Thrust Levers IDLE Gust Lock ENGAGE Doors CLSD Flaps 0 Pitch Trim AS REQUIRED To avoid APU fluid ingestion it is recommended that pitch trim should be set from 0 to FUL...

Page 278: ...TIAL CLIMB Wait at least one minute to open engine bleed and three minutes to turn air conditioning packs on thereby avoiding contaminating the airframe air conditioning system with deicing anti icing...

Page 279: ...while parked may induce vibration in the airplane Vibration should disappear as the tires recover their elasticity during taxi Do not initiate your takeoff run before the cold set disappears Maintain...

Page 280: ...and climb proceed Thrust Levers 83 N2 Ice Detection Override Knob ALL Anti Icing Buttons engine wing and stabilizer PRESSED Ice Detection Test Knob 1 THEN 2 Test knob must be held at least 10 seconds...

Page 281: ...ach side separately check that ICE DET 1 or 2 FAIL and BLD 1 or 2 LOW TEMP caution messages and ICE CONDITION advisory message are displayed on EICAS The CROSS BLD OPEN advisory message and or the PAC...

Page 282: ...test set the Ice Detection Override Knob to ENG Check that engine REF A ICE on MFD takeoff page is set to ON Ignition ON Turn ignition on when standing water ice or snow is present on the takeoff runw...

Page 283: ...performance data is valid from the point where takeoff thrust is achieved Check N1 indication consistent with takeoff thrust setting tables check AFM performance tables which have dedicated thrust set...

Page 284: ...t Levers as required to maintain ITT within limits When flying in icing conditions or after flying in icing conditions ice accretion on unprotected areas may cause vibration at high speeds If vibratio...

Page 285: ...proaching the terminal area in icing conditions an increased rate of descent may be necessary In this case a combination of flaps set at 9 and speed brakes open may be used NOTE Engine and Wing Ice Pr...

Page 286: ...the occurrence of this phenomenon are high speed standing water and poor runway macrotexture When hydroplaning occurs it causes a substantial loss of tire friction and wheel spin up may not occur Icy...

Page 287: ...AXI AT REDUCED SPEED IN ICE COVERED RUNWAYS TO AVOID SKIDDING THE AIRPLANE THROUGH FLIGHTS Doors and Windows CLOSED Whenever possible to maintain the cabin warm keep the passenger baggage and service...

Page 288: ...y Parking Brakes must not be applied to avoid freezing of the brakes Pitch Trim FULL NOSE DOWN As high precipitation may occur during overnights it is recommended that pitch trim be left at full nose...

Page 289: ...d at all times Consider turning the autopilot off if you suspect you are flying in severe icing conditions Monitor anti ice systems for proper operation Apply the associated AFM abnormal procedure in...

Page 290: ...itate to leave icing conditions when icing cannot be handled even with anti ice system operating properly NOTE Engine and Wing Ice Protection Systems operation is automatic and based on the primary ic...

Page 291: ...zle conditions as soon as possible since continuous flight under such conditions is indeed quite hazardous FLAP OPERATION UNDER ICING CONDITIONS Ice accretion on an airplane depends mainly on the clou...

Page 292: ...een 2 C and 10 C between 35 6 F and 14 F Regardless of the airplane type the wing horizontal stabilizer and engine inlets are typically critical airplane parts for ice accretion and are protected with...

Page 293: ...rspeed 2 ATTITUDE Maintain wings level and proper pitch attitude Use attitude indicator as the primary instrument In extreme drafts large attitude changes may occur Do not use sudden large control inp...

Page 294: ...these circumstances The presence of volcanic ash dust may be indicated by Smoke of dust appearing inside the airplane An acrid odor similar to electrical smoke or burnt dust or sulfur Engine malfuncti...

Page 295: ...ft of the engine inlets Use APU for engine starting only not for air conditioning Prior to starting dry motor the engine for one minute in order to blow out any ash that may have entered the engine by...

Page 296: ...strong smell of sulphur don an oxygen mask and select 100 APU START Ignitions ON Thrust Lever if altitude permits IDLE Anti Icing Buttons engine wing and stabilizer PRESSED Ice Detection Override Knob...

Page 297: ...by Embraer Refertocoverpagefor details AOM 145 1114 After exiting the area of volcanic ash dust cloud and the engine s restarted restore systems to normal operation Inform ATC of the encounter Airspe...

Page 298: ...h may lead to occasional encounters with hail and lightning Circumnavigate the detected thundercloud or area if possible by more than 25 miles when traffic conditions permit Flying over the top of the...

Page 299: ...acitation due to lightning although flash blindness can occur for a few seconds Direct effects which result from lightning current attachment to and flow through the airplane may be Pit marks are ofte...

Page 300: ...htning strike apply the following procedure to ascertain whether the flight may be proceed Circuit Breakers CHECK Compass Heading System CHECK Check magnetic compass and heading system for normal indi...

Page 301: ...ommended The human body may provide the grounding that is otherwise lacking If you are in the cockpit do not attempt to communicate with ground through a wire handset and stay inside the airplane unti...

Page 302: ...equired to control cabin altitude In manual mode crew selection of the cabin rate and proper monitoring of cabin differential pressure is required to maintain appropriate cabin pressurization With rel...

Page 303: ...Just after the initial climb Pressurization Manual Controller BETWEEN 11 AND 12 O CLOCK Keeping the manual controller within the white mark allows a null or slightly positive rate for the cabin altitu...

Page 304: ...nt Manual Controller SLOWLY TURN COUNTER CLOCKWISE Initially set 400 ft min rate which corresponds to a position between 12 and 11 o clock in the manual controller During descent Set a cabin rate that...

Page 305: ...fore entering it For entry types other than the direct one the pilot must activate the procedure holding pattern as soon as the approach procedure is retrieved from the Navigation Data Base NOTE The F...

Page 306: ...label will be always magenta For FMS coupling to the Autopilot Flight Director NAV Mode Flight Guidance Controller SELECT The FMS will be coupled to the Autopilot Flight Director when is selected and...

Page 307: ...oach APR Mode Flight Guidance Controller SELECT ARC DME APPROACH USING FMS Pilot Not flying CHECK DME During Arc DME approach using FMS the pilot not flying must check DME Raw Data MISSED APPROACH CAU...

Page 308: ...AO Regional Navigation Agreement LIMITATIONS MINIMUM EQUIPMENT REQUIRED During RVSM operation it is necessary that the following equipment and instruments be in proper operating condition 2 Primary Al...

Page 309: ...le to notify ATC and obtain an ATC clearance prior to deviating from the cleared flight level follow any established contingency procedures and obtain ATC clearance as soon as possible NORMAL PROCEDUR...

Page 310: ...at the aircraft is flown at the cleared flight level and that ATC clearances are fully understood and followed Do not depart from cleared flight level without a positive clearance from ATC except for...

Page 311: ...as necessary to correct the airplane attitude flight path and configuration according to the voice message presented to provide terrain clearance CAUTION FOR EGPWS THE TERRAIN DISPLAY IS INTENDED TO B...

Page 312: ...e traffic Compliance with TCAS resolution advisory is required unless the pilot considers it unsafe to do so Maneuvers which are in the opposite direction of the RA are extremely hazardous especially...

Page 313: ...or overlay approaches airworthiness of airplane systems and aircrew qualification Pilots should assess their capability to navigate potentially to an alternate destination in case of GPS outages or pr...

Page 314: ...in the following table DEVIATION ENROUTE nm TERMINAL nm APPROACH nm 0 0 0 0 1 dot 2 5 0 5 0 15 2 dots 5 0 1 0 0 30 NOTE In the PFD display the phases of flight are identified as follows Terminal phase...

Page 315: ...in the case of loss of RNP APCH airborne this equipment may be required to comply with this condition This equipment may also be required to comply with the missed approach procedure if it is based o...

Page 316: ...not permitted Slight differences between the navigation information portrayed in the chart and CDI magenta may occur Differences of 3 or less are considered acceptable LNAV Mode AS REQUIRED GPS is in...

Page 317: ...lid In any case if not visual perfom a missed approach using alternate sources VOR NDB or visual references DEGRADED NAVIGATION The navigation will be degraded whenever the FMS cannot guarantee that t...

Page 318: ...ration of the flight NOTE If the AIRAC cycle will change during the flight the locations of the waypoints used to define procedures must be verified with current navigational charts GENERAL GUIDANCE W...

Page 319: ...or P RNAV operations VOR DME may be used as a sensor for positioning 1 Dual FMS is required 2 Off Line RAIM prediction is required 3 This operation is permitted up to 6 2 hours after the system is pla...

Page 320: ...asic RNAV systems with no further substantiation According to AFM the EMB 145 RNAV system installation is compliant with AC 20 130A 6 NO AFM STATMENT The AC 90 100A compliance table lists that the EMB...

Page 321: ...y inappropriate or inadvertent position shift after takeoff Where GNSS is used the signal must be acquired before the takeoff roll commences and GNSS position may be used instead of runway update Wher...

Page 322: ...V procedure is not available Airplane Minimum Configuration CHECK Check if the airplane configuration complies with the applicable list below For all but RNAV 10 operations 1 GPS 1 VOR 1 DME 1 IRS 1 F...

Page 323: ...terminal airspace procedures for the departure arrival and alternate airfields In this case affected procedures must be prohibited by an operator s notice to the flight crew RNAV System if required CO...

Page 324: ...Configuration VERIFY AVAILABILITY Also where applicable verify if the correct airport and runway data have been loaded Flight Progress MONITOR During the procedure and where feasible monitor navigati...

Page 325: ...th the RNAV control and display unit CDU REMOTE ENROUTE RNAV 10 Dual FMS and GPS CHECK AVAILABILITY At least two FMS and two GPS must be operational at the oceanic entry point If this is not the case...

Page 326: ...and where feasible monitor navigation reasonableness by cross checks with the conventional NAVAIDs using the primary displays with the MCDU NOTE When the contingency plan is to revert to a convention...

Page 327: ...ing an alternative means of navigation The alternate means does not need to be based on RNAV system NAVIGATION SENSORS FAILURE Discontinue the RNAV procedure following the approved missed approach pro...

Page 328: ...clare Missed Approach Non RNP Remote Crosscheck FMS data with raw data from GPS or IRS De select error causing sensor if detectable FMS 1 2 FAILURE Select the cross side FMS In case both FMS are unava...

Page 329: ...during RNAV operations which lead to Navigations errors not associated with transitions between different navigation modes Significant navigation errors attributed to incorrect data or a navigation d...

Page 330: ...SUPPLEMENTARY PROCEDURES NAVIGATION AIRPLANE OPERATIONS MANUAL 1 02 80 Page 26 Code 01 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 331: ...dures HOLDING If a Holding Pattern entering is necessary FMS AS REQUIRED The pilot must check the entry type and turn direction of holding pattern before entering it For entry types other than the dir...

Page 332: ...es Post Mod SB 145 22 0001 or with an equivalent modification factory incorporated the FMS label will be always magenta On MFD the label will be always magenta For FMS coupling to the Autopilot Flight...

Page 333: ...e will appear on the PFD VS or Pitch Hold Mode SELECT AS REQUIRED Use VS or pitch hold mode mode as required to fly the VNAV flight path HEADING VECTORS If the airplane is given heading vectors by ATC...

Page 334: ...ACH USING FMS Pilot Not flying CHECK DME During Arc DME approach using FMS the pilot not flying must check DME Raw Data MISSED APPROACH Go Around Button PRESS Thrust Levers MAX Verify that airplane ro...

Page 335: ...that the following equipment and instruments be in proper operating condition 2 Primary Altitude Measurement Systems 1 Autopilot with Altitude Hold Mode operative 1 Altitude Alerter 1 Transponder NOTE...

Page 336: ...le to notify ATC and obtain an ATC clearance prior to deviating from the cleared flight level follow any established contingency procedures and obtain ATC clearance as soon as possible NORMAL PROCEDUR...

Page 337: ...at the aircraft is flown at the cleared flight level and that ATC clearances are fully understood and followed Do not depart from cleared flight level without a positive clearance from ATC except for...

Page 338: ...as necessary to correct the airplane attitude flight path and configuration according to the voice message presented to provide terrain clearance CAUTION FOR EGPWS THE TERRAIN DISPLAY IS INTENDED TO B...

Page 339: ...e traffic Compliance with TCAS resolution advisory is required unless the pilot considers it unsafe to do so Maneuvers which are in the opposite direction of the RA are extremely hazardous especially...

Page 340: ...for overlay approaches airworthiness of airplane systems and aircrew qualification Pilots should assess their capability to navigate potentially to an alternate destination in case of GPS outages or p...

Page 341: ...the following table DEVIATION ENROUTE nm TERMINAL nm APPROACH nm 0 0 0 0 1 dot 2 5 0 5 0 15 2 dots 5 0 1 0 0 30 NOTE In the PFD display the phases of flight are identified as follows Terminal phase is...

Page 342: ...omply with this condition This equipment may also be required to comply with the missed approach procedure if it is based on conventional navaids NAV Database VERIFY CURRENCY Verify that the Navigatio...

Page 343: ...not permitted Slight differences between the navigation information portrayed in the chart and CDI magenta may occur Differences of 3 or less are considered acceptable LNAV Mode AS REQUIRED GPS is in...

Page 344: ...not automatically removed from the PFD If any of these situations happens if not visual declare missed approach DEGRADED NAVIGATION The navigation will be degraded whenever the FMS cannot guarantee th...

Page 345: ...ration of the flight NOTE If the AIRAC cycle will change during the flight the locations of the waypoints used to define procedures must be verified with current navigational charts GENERAL GUIDANCE W...

Page 346: ...Dual FMS is required 2 Off Line RAIM prediction is required 3a According to AC 90 96A the airplane should be considered eligible for B RNAV RNAV 5 operations if the AFM shows the appropriate instrumen...

Page 347: ...Where GNSS is used the signal must be acquired before the takeoff roll commences and GNSS position may be used instead of runway update Where reliance is placed on the use of radar to assist continge...

Page 348: ...Configuration CHECK Check if the airplane configuration complies with the applicable list below For all but RNAV 10 operations 1 GPS 1 FMS 1 CDU 4 Display units 1 Flight Director For RNAV 10 operation...

Page 349: ...5 1114 RNAV System if required CONFIRM AVAILABILITY When dual RNAV system is required on the AIP RAIM if applicable CONFIRM AVAILABILITY Confirmation is necessary if a stand alone GPS is to be used fo...

Page 350: ...rplane Minimum Configuration VERIFY AVAILABILITY Also where applicable verify if the correct airport and runway data have been loaded NOTE Where GNSS is used the signal must be acquired before the tak...

Page 351: ...th the RNAV control and display unit CDU REMOTE ENROUTE RNAV 10 Dual FMS and GPS CHECK AVAILABILITY At least two FMS and two GPS must be operational at the oceanic entry point If this is not the case...

Page 352: ...lar NAVAID A procedure shall not be used in case of doubt regarding the procedure in the navigation database Flight Progress MONITOR During the procedure and where feasible monitor navigation reasonab...

Page 353: ...ing an alternative means of navigation The alternate means does not need to be based on RNAV system NAVIGATION SENSORS FAILURE Discontinue the RNAV procedure following the approved missed approach pro...

Page 354: ...clare Missed Approach Non RNP Remote Crosscheck FMS data with raw data from GPS or IRS De select error causing sensor if detectable FMS 1 2 FAILURE Select the cross side FMS In case both FMS are unava...

Page 355: ...during RNAV operations which lead to Navigations errors not associated with transitions between different navigation modes Significant navigation errors attributed to incorrect data or a navigation d...

Page 356: ...SUPPLEMENTARY PROCEDURES NAVIGATION AIRPLANE OPERATIONS MANUAL 1 02 80 Page 26 Code 02 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 357: ...ng engine using the LPU or to perform a crossbleed start The engines pneumatic start does not affect the electrical system or the individual loads connected to it The voltage of the buses fed by the b...

Page 358: ...Beacon ON Fuel Pump associated engine ON Start Pressure AVAILABLE START Start Stop Selector associated engine START THEN RUN Turn the start selector to RUN for 2 seconds then turn the switch to the ST...

Page 359: ...to the FADEC and then to RUN and start the stopwatch Engine Indication MONITOR NOTE After the start is completed reduce operating engine power to idle ENGINE START ASSISTED BY THE APU This procedure m...

Page 360: ...ing under MEL with one engine driven generator inoperative choose the engine which has both generators operating NOTE Batteries charge may be preserved by using all available generators AFTER START FA...

Page 361: ...TER LANDING Shed Buses OVRD Electric Hydraulic Pumps AUTO Air Conditioning and Pneumatic System AS REQUIRED Selected Engine SHUTDOWN ABNORMAL PROCEDURES If the operating engine fails stop the airplane...

Page 362: ...SUPPLEMENTARY PROCEDURES ENGINE AIRPLANE OPERATIONS MANUAL 1 02 81 Page 6 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 363: ...d 2 altimeters and between these and the standby system altimeter with the airplane on ground or in flight can occur due to a number of reasons and may vary with altitude airspeed and airplane configu...

Page 364: ...pare the difference between altitudes using the following table ALTITUDE ft MAXIMUM DIFFERENCE BETWEEN PILOT AND COPILOT S ALTIMETERS ft MAXIMUM DIFFERENCE BETWEEN PILOT OR COPILOT S ALTIMETERS AND ST...

Page 365: ...dio Altimeter is checked not functioning properly the CAT ll approach must discontinued A minimum distance of 4 NM to the Outer Marker is recommended for interception and stabilization along the appro...

Page 366: ...tting the GPWS will call out APPROACHING MINIMUM At the decision height setting the GPWS will call out MINIMUM and the pilot not flying will call out LANDING or GO AROUND as appropriate If visual cont...

Page 367: ...Y NORMAL PROCEDURES CAT II OPERATION REVISION 38 1 02 83 Page 3 Code 02 AOM 145 1114 MISSED APPROACH GO AROUND Procedure ACCOMPLISH LANDING Reaching the Decision Height with runway in sight Autopilot...

Page 368: ...SUPPLEMENTARY NORMAL PROCEDURES CAT II OPERATION AIRPLANE OPERATIONS MANUAL 1 02 83 Page 4 Code 02 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 369: ...CAT IIIa operation is predicated upon the use of an ILS facility with performance and integrity equivalent to or between an ICAO Annex 1 Facility Performance CAT III ILS an US Type II or Type III ILS...

Page 370: ...AND LANDING CONDITIONS OF OPERATION The system conditions that must be met in order to achieve AIII capability include IRS in NAV mode AHRS 2 in Full Performance mode NOTE AHRS is not applicable in c...

Page 371: ...procedures and performance data contained in the basic AOM When using PRI or IMC modes to monitor autopilot coupled approaches refer to the CAT II limitations emergency and abnormal procedures in the...

Page 372: ...ET HGS Control Panel HGS Mode PRI RUNWAY LENGTH SET RUNWAY ELEVATION SET GLIDESLOPE SET Display Control Panel 1 SET TO NAV 1 Display Control Panel 2 SET TO NAV 2 ALL 3 NAV Receivers SET TO ILS Course...

Page 373: ...ADJUST CAUTION RUNWAY REMAINING IS A SUPPLEMENTAL SITUATION AWARENESS DISPLAY DECREASING IN 500 FT INCREMENTS AVAILABLE IN LOW VISIBILITY TAKEOFF THE DATA DISPLAYED IS NOT INTENDED TO BE USED FOR PER...

Page 374: ...K RUNWAY ELEVATION CHECK GLIDESLOPE CHECK Flaps 22 Speed SET AIII VAPP NOTE The AIII VAPP is determined by adjusting the VAPP for head wind component and gust according to the following equation AIII...

Page 375: ...FT INCREMENTS AVAILABLE AFTER TOUCHDOWN IN AIII MODE THE DATA DISPLAYED IS NOT INTENDED TO BE USED FOR PERFORMANCE MONITORING PURPOSES PRIMARY IMC OR VMC APPROACH Course Selector 1 SET TO RUNWAY HEAD...

Page 376: ...n Advisories provided are similar to MFD indications Preventive Advisories do not require that action be taken by the crew to alter the flight path of the airplane but indicate an unsafe zone Correcti...

Page 377: ...145 21 0050 NOTE During high altitude operations at least one pilot is required to use oxygen continuously until the cabin altitude has reached 8000 ft BEFORE START Pressurization 8000 FT If flying f...

Page 378: ...SUPPLEMENTARY PROCEDURES HIGH ALTITUDE OPERATION AIRPLANE OPERATIONS MANUAL 1 02 87 Page 2 Code 01 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 379: ...ed in the basic AOM The remaining Normal Procedures section remains unchanged BEFORE START Pressurization 8000 ft NOTE In airports with pressure altitude between 8000 ft and 8500 ft the cabin altitude...

Page 380: ...SUPPLEMENTARY PROCEDURES OPERATION IN AIRPORTS UP TO 8500 FT AIRPLANE OPERATIONS MANUAL 1 1 02 92 Page 2 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 381: ...Flaring high and quickly reducing thrust to idle can cause the plane to settle abruptly Do not apply stabilizer trim during the flare When a light bounce occurs maintain or re establish a normal land...

Page 382: ...SUPPLEMENTARY PROCEDURES BOUNCED LANDING RECOVERY AIRPLANE OPERATIONS MANUAL 1 02 94 Page 2 Code 01 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 383: ...14 THRUST SET THRUST LEVERS 2 WHEN OUTBOUND HEADING IS ESTABLISHED CONSIDER USING VFS MINIMUM FLAP RETRACTION SPEED SCHEDULE AFTER TAKEOFF CHECKLIST AFTER TAKEOFF CHECKLIST MAINTAIN V 15 SELECT FLAPS...

Page 384: ...HED CONSIDER USING VFS MINIMUM FLAP RETRACTION SPEED SCHEDULE AFTER TAKEOFF CHECKLIST AFTER TAKEOFF CHECKLIST MAINTAIN V 15 CLIMB SEQUENCE CLIMB SEQUENCE RETRACT FLAPS ACCORDING TO THE SCHEDULE CLIMB...

Page 385: ...HEDULE AFTER TAKEOFF CHECKLIST AFTER TAKEOFF CHECKLIST MAINTAIN V 15 CLIMB SEQUENCE CLIMB SEQUENCE RETRACT FLAPS ACCORDING TO THE SCHEDULE CLIMB THRUST SPEED 210 KT RETRACT FLAPS ACCORDING TO THE SCHE...

Page 386: ...EVISION 36 AOM 145 1114 THRUST SET 80 Knots V1 ROTATE POSITIVE RATE AT 1500 AFE AT 3000 AFE SET SPEED TARGET AS REQUIRED RETRACT FLAPS ON SCHEDULE NOISE ABATEMENT TAKEOFF A GEAR UP V2 10 Knots SELECT...

Page 387: ...Code 05 AOM 145 1114 THRUST SET 80 Knots V1 ROTATE POSITIVE RATE AT 3000 AFE NOISE ABATEMENT TAKEOFF B GEAR UP V2 10 Knots AT 1000 AFE SET SPEED TARGET AS REQUIRED SELECT CLB THRUST AND RETRACT FLAPS...

Page 388: ...TE OF CLIMB PRECISION APPROACH ILS BEFORE LANDING CHECKLIST GEAR UP 200 KIAS IN ICING CONDITIONS FLAPS 9 160 KIAS HOLDING SPEED 180 KIAS EM145AOM021003A DGN PUSH GO AROUND BUTTON ACCELERATION ALTITUDE...

Page 389: ...G SPEED 180 KIAS FLAPS 22 OR 45 FLAPS 9 MAXIMUM THRUST POSITIVE RATE OF CLIMB GEAR UP PUSH GO AROUND BUTTON ACCELERATION ALTITUDE RETRACT FLAPS ACCORDING TO THE SCHEDULE AFTER TAKEOFF CHECKLIST COMPLE...

Page 390: ...MPLETE DESCENT APPROACH FLAPS 0 GEAR UP CHECKLIST EM145AOM021012A DGN 1 5 nm 30 s REF FLAPS 9 MAXIMUM THRUST POSITIVE RATE OF CLIMB GEAR UP PUSH GO AROUND BUTTON ACCELERATION ALTITUDE CLIMB SEQUENCE A...

Page 391: ...CIRCLING ALTITUDE MUST BE MAINTAINED MISSED APPROACH POINT THE CIRCLING MANEUVER USE OF AUTOPILOT IS RECOMMENDED V REF FLAPS 9 MAXIMUM THRUST POSITIVE RATE OF CLIMB GEAR UP PUSH GO AROUND BUTTON ACCEL...

Page 392: ...LIMB THRUST LEVERS THRUST SET ROTATE TO 14 2 V COMPLETE APPLICABLE CHECKLIST GEAR UP ALT HOLD AFTER TAKEOFF CHECKLIST 1 FLAP RETRACTION SPEED SCHEDULE 2 FS CLIMB AT V FS IAS MODE V 2 LATERAL MODE ACCO...

Page 393: ...AS CHECKLIST FLAPS 0 GEAR UP FLAPS 22 FINAL FLAP SETTING ONE ENGINE INOPERATIVE VISUAL APPROACH COMPLETE DESCENT APPROACH 500 800 ft 1 5 nm 30 s FLAPS 9 MAXIMUM THRUST POSITIVE RATE OF CLIMB GEAR UP P...

Page 394: ...LAPS 22 FINAL FLAP SETTING GEAR UP FLAPS 0 200 KIAS IN ICING CONDITIONS HOLDING SPEED 180 KIAS BEFORE LANDING CHECKLIST AFTER ESTABLISHED ON GLIDE SLOPE SET GO AROUND ALTITUDE V REF APP FLAPS 9 MAXIMU...

Page 395: ...PS 22 FINAL FLAP SETTING GEAR UP 200 KIAS IN ICING CONDITIONS HOLDING SPEED 180 KIAS PUSH GO AROUND BUTTON ACCELERATION ALTITUDE ALT HOLD END OF TAKEOFF PATH THRUST RATING CON COMPLETE APPLICABLE CHEC...

Page 396: ...ING TO THE TYPE OF APPROACH CIRCLING ALTITUDE MUST BE MAINTAINED MISSED APPROACH POINT ONE ENGINE INOPERATIVE CIRCLING APPROACH THE CIRCLING MANEUVER FLAPS 9 MAXIMUM THRUST POSITIVE RATE OF CLIMB GEAR...

Page 397: ...OF THE PILOT S EYE ABOVE THE WHEELS R HEIGHT OF GLIDE RECEIVER ANTENNA ABOVE THE WHEELS AIRPLANE ATTITUDE DEGREES P FEET R FEET 23 0 14 4 PILOT EYE POSITION GROUND 3 0 4 4 14 6 11 0 4 9 14 9 11 4 2 5...

Page 398: ...P FEET R FEET 3 0 3 8 13 7 10 0 4 3 14 1 10 4 2 5 GLIDE SLOPE ANGLE DEGREES R P G LI DE SL O PE PA TH GLIDE SLOPE ANGLE P HEIGHT OF THE PILOT S EYE ABOVE THE WHEELS R HEIGHT OF GLIDE RECEIVER ANTENNA...

Page 399: ...P FEET R FEET 3 0 3 8 13 7 10 0 4 3 14 1 10 4 2 5 GLIDE SLOPE ANGLE DEGREES R P G LI DE SL O PE PA TH GLIDE SLOPE ANGLE P HEIGHT OF THE PILOT S EYE ABOVE THE WHEELS R HEIGHT OF GLIDE RECEIVER ANTENNA...

Page 400: ...FEET R FEET 3 0 5 3 15 2 11 8 5 8 15 6 12 2 2 5 GLIDE SLOPE ANGLE DEGREES R P G LI DE SL O PE PA TH GLIDE SLOPE ANGLE P HEIGHT OF THE PILOT S EYE ABOVE THE WHEELS R HEIGHT OF GLIDE RECEIVER ANTENNA A...

Page 401: ...0 200 20000 UP 6 3 53 6 0 180 20000 UP 6 3 53 6 0 180 20000 UP 6 4 55 3 9 160 20000 UP 6 6 57 2 18 150 20000 UP 6 8 59 8 22 140 19000 DN 3 7 66 9 9 180 19000 DN 5 1 65 4 18 160 19000 DN 6 4 64 2 22 1...

Page 402: ...NORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 02 95 Page 20 Code 05 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 403: ...ncy Procedures Doors 1 03 01 Crew Awareness 1 03 02 Electrical 1 03 03 Fire Protection 1 03 05 Fuel 1 03 07 APU 1 03 09 Powerplant 1 03 11 Landing Gear 1 03 14 Flight Controls 1 03 20 Air Conditioning...

Page 404: ...1 03 53 Air Conditioning Pneumatics and Pressurization 1 03 56 Ice Protection 1 03 57 Oxygen 1 03 58 Navigation 1 03 59 Autopilot 1 03 60 CAT II Operation 1 03 65 HGS Operation 1 03 66 Steep Approach...

Page 405: ...bility to use good judgement concerning the time and place to land as well as to evaluate factors such as airplane condition weather etc The decision to reject takeoff should be considered if any unde...

Page 406: ...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 ar...

Page 407: ...scription on MFD are displayed in red Fasten Seat Belts ON Check doors pictorial indication on MFD Takeoff Page If message is confirmed or if MFD is not available Door Internal Lock Indicators red mar...

Page 408: ...EMERGENCY PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 01 Page 2 Code 03 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 409: ...peed V REF 45 5 KIAS CAUTION TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45 BY 1 10 STICK PUSHER FAILURE EICAS WARNING SPS 1 2 INOP EICAS CAUT...

Page 410: ...rt ceases EGPWS GPWS WARNING If an EGPWS GPWS WARNING occurs and unless operating in visual meteorological condition VMC and or the pilot determines based on all available information that a turning i...

Page 411: ...L TERRAIN CLEARANCE IS ASSURED TRAFFIC AND COLLISION AVOIDANCE AURAL WARNING According to the Traffic Advisory TA and Resolution Advisory RA associated The pilot must not initiate evasive maneuvers us...

Page 412: ...ERATIONS MANUAL 1 03 02 Page 4 Code 03 REVISION 40 AOM 145 1114 AIRPLANE OVERSPEED AURAL WARNING Voice Message HIGHSPEED LIGHT Master Warning INDICATION Airspeed and Mach indications on PFD enter the...

Page 413: ...is on If the associated BATT OFF BUS message is not on land at the nearest suitable airport ELECTRIC ESSENTIAL TRANSFER FAILURE EICAS WARNING ELEC ESS XFR FAIL LIGHT Master Warning If no generator is...

Page 414: ...Power ON Crew Oxygen AS REQUIRED Passenger Oxygen AS REQUIRED Emergency Lights OFF If required turn on Emergency Lights before landing Land at the nearest suitable airport Landing Gear DOWN FLAPS POS...

Page 415: ...SPS 1 2 INOP and ICE COND A I INOP The following caution messages will be presented STICK PUSHER FAIL SPS ADVANCED GPWS INOP WINDSHEAR INOP CHECK PFD 1 IC BUS FAIL APU GEN OFF BUS GEN 1 2 3 4 OFF BUS...

Page 416: ...EMERGENCY PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 03 Page 4 Code 03 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 417: ...or smoke procedures even though smoke has dissipated land at the nearest suitable airport unless it can be visually verified that the fire has been extinguished SMOKE EVACUATION CONDITION Smoke concen...

Page 418: ...entral Pump Selector Button EMB 145XR only SET TO B Fuel Pumps 1B AND 2A OR 2C Battery 2 AUTO Battery 1 OFF Generators 1 and 3 OFF If smoke does not stop or decrease after a reasonable time restore po...

Page 419: ...OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE LAVATORY SMOKE EICAS WARNING LAV SMOKE LIGHT Master Warning Lavatory Flush Lavatory Light CB s E11 and E12 PULL CABIN FIRE OR SMOKE Procedure A...

Page 420: ...EMERGENCY PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 05 Page 4 Code 03 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 421: ...supplies fuel to the APU The pilot may consider to shutdown the engine if fuel leakage continues and is severe Associated Thrust Lever IDLE Start Stop Selector STOP NOTE Engine will not shutdown with...

Page 422: ...on enters in red range Thrust Levers REDUCE TO LONG RANGE SET Level the airplane and check both fuel quantities If fuel quantity is sufficient complete the flight normally If fuel quantity is not suff...

Page 423: ...ge remains Right Electric Fuel Pumps OFF Crossfeed OFF Initiate a descent to 25000 ft or MEA whichever is higher After 30 seconds if the APU FIRE message remains displayed or if the APU FIREDET FAIL m...

Page 424: ...EMERGENCY PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 09 Page 2 Code 03 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 425: ...E If the fire message remains displayed on EICAS after 30 seconds from 1 st shot Fire Extinguishing Handle 2 nd shot ROTATE If E1 2 FUELSOV CLSD advisory message is not displayed on the EICAS Crossfee...

Page 426: ...TIONS PROCEDURE NOTE If in flight below 9700 ft the air conditioning pack valves may close automatically The APU may be used as pneumatic source by closing the remaining engine bleed valve Engine will...

Page 427: ...ows Thrust Levers MAX Check engine parameters If engine parameters are within normal range another takeoff may be attempted Alternate Takeoff modes are prohibited CAUTION BRAKES TEMPERATURE MUST BE CH...

Page 428: ...1 and 2 will be available Engine windmilling should drive engine driven pumps and supply hydraulic pressure If neither engine can be restarted FORCED LANDING Procedure ACCOMPLISH ENGINE OIL LOW PRESS...

Page 429: ...Associated Thrust Lever IDLE Airspeed MAXIMUM 200 KIAS PRECAUTIONARY ENGINE SHUTDOWN Procedure ACCOMPLISH Land at the nearest suitable airport REJECTED TAKEOFF AT OR BELOW V1 CONDITION In the event of...

Page 430: ...uvering is required maintain a maximum bank of 15 During takeoff with flaps 9 when reaching the level off height At V2 15 KIAS Flaps UP Airspeed ACCELERATE TO FINAL SEGMENT SPEED During takeoff with f...

Page 431: ...aps 9 or 12 flaps 18 With positive rate of climb Landing Gear UP Airspeed V2 Maintain V2 up to the level off altitude If maneuvering is required maintain a maximum bank of 15 During takeoff with flaps...

Page 432: ...EMERGENCY PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 11 Page 8 Code 03 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 433: ...aster Warning EICAS Indication Landing gear indication may be present one or more boxes cross hatched or red Landing Gear CYCLE If the message persists In a retraction Landing Gear DOWN Airspeed MAXIM...

Page 434: ...EMERGENCY PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 14 Page 2 Code 03 REVISION 17 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 435: ...tch and respective trim pictorial indication changes Quick Disconnect Button PRESS AND HOLD NOTE Do not change flap setting At safe altitude Pitch Trim Main System OFF Pitch Trim Back Up System OFF Qu...

Page 436: ...any Pitch Trim Switch Airspeed REDUCE Airspeed reduction alleviates control column forces and may permit Pitch Trim command to be recovered If Pitch Trim command is reestablished continue using the r...

Page 437: ...ding at the nearest suitable airport Approach and landing configuration Landing Gear DOWN Flaps 22 Airspeed VREF 45 10 KIAS CAUTION TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE MULTIPLY THE UNFA...

Page 438: ...If Pitch Trim command is reestablished continue using the remaining Pitch Trim System NOTE Do not engage the Autopilot if the Main Pitch Trim System is inoperative If only one segment of the Pitch Tri...

Page 439: ...UITABLE LANDING DISTANCE MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45 BY 1 45 If pitch trim command is not reestablished and the airplane presents a NOSE DOWN tendency Airspeed REDUCE Below 2...

Page 440: ...ct PULL Autopilot OFF Airspeed MAXIMUM 200 KIAS Pitch Trim AS REQUIRED Avoid landing at airports with anticipated turbulence or crosswind Approach and landing configuration Landing Gear DOWN Flaps 22...

Page 441: ...tem Prepare to overcome the roll generated by the failed aileron system If the failure is confirmed in one aileron system the roll trim system may be used as required If the message AIL SYS 1 2 INOP i...

Page 442: ...al feel are available If the pilot s aileron is operative roll trim and artificial feel are not available Do not make sudden and large aileron inputs Do not increase bank angle above 20 Airspeed MAXIM...

Page 443: ...FACTORED LANDING DISTANCE FOR FLAPS 45 BY 1 62 If required use asymmetric thrust to trim the airplane directionally and maintain the engine thrust until nose gear contact in order to avoid lateral and...

Page 444: ...und Spoiler Inboard Circuit Breaker F21 PULL If any panel is jammed closed open or is floating Approach and landing configuration Landing Gear DOWN Flaps 22 Airspeed VREF 45 10 KIAS Do not reduce engi...

Page 445: ...eck APU bleed button not illuminated Altitude MAX 25000 ft MINIMUM MEA Icing Conditions EXIT AVOID Wait 3 minutes If the message remains on but the associated advisory message on EICAS BLD 1 or 2 VLV...

Page 446: ...side Bleed OPEN Associated Bleed CLOSE Altitude MAX 25000 ft MINIMUM MEA WARNING IF IN ICING CONDITIONS REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE RAPID CABIN DEPRE...

Page 447: ...ob 1 THEN 2 Test knob must be held for 5 seconds in each test position For each side separately check that OPEN inscriptions in the anti icing buttons are flashing and that ICE DET 1 or 2 FAIL caution...

Page 448: ...EMERGENCY PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 24 Page 4 Code 03 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 449: ...ILURE EICAS WARNING AUTOPILOT FAIL LIGHT Master Warning AURAL WARNING AUTOPILOT only below 2500 ft radio altitude when autopilot is disconnected Autopilot DISENGAGE Trim the airplane as required NOTE...

Page 450: ...EMERGENCY PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 26 Page 2 Code 03 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 451: ...THAT THE INTEGRITY OF THE STRUCTURE IS NOT AFFECTED IF STRUCTURAL DAMAGE IS SUSPECTED USE THE FLIGHT CONTROLS WITH CAUTION AVOIDING HIGH MANEUVERING LOADS AND REDUCING AIRSPEED AS APPROPRIATE NOTE It...

Page 452: ...Flaps 45 If it is not possible to achieve the selected flap position maintain airspeed according to the following FLAPS POSITION MINIMUM AIRSPEED 0 to 8 VREF 45 30 KIAS 9 to 21 VREF 45 10 KIAS 22 to...

Page 453: ...s When reaching 1000 ft Ventral Tank Transfer Knob EMB 145XR only OFF Air Conditioning 1 and 2 OFF Engine Bleeds CLOSE Approach configuration Landing Gear UP Flaps 45 If it is not possible to achieve...

Page 454: ...NG DOORS EMERGENCY EVACUATION Parking Brake if necessary APPLY Cabin DEPRESSURIZE Fire Extinguishing Handles PULL APU Fuel Shutoff Valve CLOSE APU and Engine Fire Extinguishing Bottles if necessary DI...

Page 455: ...from the seats near the associated emergency exit If emergency exit is not confirmed locked or it is not possible to maintain the pressurization Altitude MEA OR 10000 ft WHICHEVER IS HIGHER Cabin Pres...

Page 456: ...7 MAIN DOOR BLOCKED LIGHT Door Blocked Closed Attendant s panel To open the door on ground Check that the door opening area is free of both people and ground equipment Hydraulic System 1 OFF Main Door...

Page 457: ...irspeed VREF 45 5 KIAS CAUTION TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45 BY 1 10 ADVANCED STALL PROTECTION EICAS CAUTION SPS ADVANCED LIG...

Page 458: ...r TERR INOP for EGPWS LIGHT Master Caution Monitor any trend toward terrain contact excessive sink rate marginal flight path and airplane configuration Do not perform CAT II approaches AURAL WARNING F...

Page 459: ...N BKUP BATT OFF BUS Backup Battery VERIFY ON BATTERY OFF BUS EICAS CAUTION BATT 1 2 OFF BUS LIGHT Master Caution Affected Battery AUTO DC BUS OFF EICAS CAUTION DC BUS 1 2 OFF LIGHT Master Caution Bus...

Page 460: ...AUTION ELEC EMERG ABNORM LIGHT Master Caution Essential Power CHECK OFF If message persists Land at the nearest suitable airport Bus Ties OFF Batteries 1 and 2 OFF If message persists Bus Ties AUTO Ba...

Page 461: ...ICING CONDITIONS REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE COM 2 on Digital Audio Panel 2 PUSH IN Monitor fuel quantity indication 1 through FMS Brake effectivene...

Page 462: ...2C Icing Conditions EXIT AVOID Altitude MAX 25000 FT MINIMUM MEA Monitor fuel quantity indication 2 through FMS Brake effectiveness will be reduced When necessary to extend landing gear ABNORMAL LAND...

Page 463: ...essential bus is off Associated ESS BUS OFF Procedure ACCOMPLISH If only DC BUS 2 is energized Battery 2 OFF Check which essential bus is off Associated ESS BUS OFF Procedure ACCOMPLISH GENERATOR BEAR...

Page 464: ...mains Electrical Load on affected generator REDUCE If APU generator is not affected and any generator is overloaded APU Generator ON SHED BUS OFF EICAS CAUTION SHED BUS 1 2 OFF LIGHT Master Caution If...

Page 465: ...S OCTOBER 02 2001 1 03 38 Page 1 Code 03 LIGHTING EMERGENCY LIGHTS NOT ARMED EICAS CAUTION EMERG LT NOT ARMD LIGHT Master Caution Emergency Lighting Selector ARM If unsuccessful check that Attendant E...

Page 466: ...ABNORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 38 Page 2 Code 03 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 467: ...iated Start Stop Selector STOP Associated Fire Extinguishing Handle PULL DO NOT ROTATE NOTE If fire is not extinguished while the engine is motored ground personnel support must be requested FIRE DETE...

Page 468: ...LIGHT Master Caution CONDITION Associated bottle has not been discharged intentionally On Engines Only one discharge will be available from the remaining bottle to protect both engines against fire On...

Page 469: ...EMP or E1 2 FUEL LO TEMP LIGHT Master Caution CONDITION Fuel temperature in amber range WARNING IF FUEL TANK LO TEMP MESSAGE IS PRESENTED IN ANY CASE OR E1 2 FUEL LO TEMP IS PRESENTED WITHOUT ICING IN...

Page 470: ...or positive locking before takeoff If the message remains repair is required before takeoff ENGINE FUEL SHUTOFF VALVE FAILURE EICAS CAUTION E1 2 FUEL SOV INOP LIGHT Master Caution Confirm the failed v...

Page 471: ...N APU FUEL SOV INOP LIGHT Master Caution Check that APU Fuel Shutoff Button is not pressed If valve remains closed and it is not possible to restart the APU APU Master Knob OFF If APU is running norma...

Page 472: ...nts lower level Crossfeed Selector LOW1 If right wing presents lower level Crossfeed Selector LOW2 Avoid rapid thrust levers movement Monitor fuel imbalance When the desired balance is achieved Crossf...

Page 473: ...the APU EGT enters the red or amber range apply the APU OVERTEMPERATURE Procedure If RPM enters red range APU SHUTDOWN APU AUTOMATIC SHUTDOWN EICAS CAUTION APU FAIL LIGHT Master Caution If shutdown o...

Page 474: ...ABNORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 41 Page 2 Code 03 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 475: ...O 1 or CON mode For AE3007A1 engines and AE3007A or AE3007A1 1 engines Post Mod SB 145 73 0010 below 9700 ft TAT above 19 C at sea level decreasing linearly to 5 C at 9700 ft and the remaining engine...

Page 476: ...KEOFF WITH ENGINE FAILURE Procedure NOTE Limiting bank angle to 5 towards operative engine improves climb performance During GO AROUND procedure the DON T SINK aural warning may sound In this case mon...

Page 477: ...start limit N2 remains steady or decreases for more than 30 seconds after light off N2 indicates no rotation up to 10 seconds after the start command Any unusual noise or vibration occurs Engine instr...

Page 478: ...er start FADEC Control Knob ALTN Check alternation of FADEC in control indication on the EICAS CAUTION IF FADEC DOES NOT ALTERNATE DO NOT PROCEED WITH THE ENGINE DRY MOTORING Ignition OFF Check IGN OF...

Page 479: ...ne Thrust Rating CON Verify N2 and ITT decreasing below IDLE values APU START APU Bleed AS REQUIRED Crossbleed AS REQUIRED Land at the nearest suitable airport TCAS TA ONLY WARNING IF IN ICING CONDITI...

Page 480: ...ABNORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 45 Page 6 Code 03 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 481: ...BLEED START TO AVOID LOSS OF ANTI ICE SYSTEM PERFORMANCE Assisted start Crossbleed start N2 operating engine ABOVE 80 Crossbleed AUTO OR OPEN Engine Bleed operating engine OPEN Start Stop Selector STA...

Page 482: ...p AUTO Windmilling start Airspeed ABOVE 260 KIAS Minimum N2 10 Start Stop Selector START THEN RUN ITT and N2 MONITOR Observe limits Abort start immediately if an Abnormal Engine Start is detected NOTE...

Page 483: ...ED FROM PREVIOUS PAGE ENGINE AIRSTART ENVELOPE 0 5000 10000 15000 20000 25000 30000 0 50 100 150 200 250 300 350 ALTITUDE FT 145CTA57 25JUL2000 INDICATED AIRSPEED KIAS AE3007A ENGINES ONLY ASSISTED ST...

Page 484: ...ture within limits If oil temperature remains high above 25000 ft Altitude MAX 25000 ft MINIMUM MEA Monitor oil temperature for the remainder of the flight If limits cannot be maintained perform a pre...

Page 485: ...X 25000 ft Exit and avoid icing conditions ENGINE REFERENCE ANTI ICE DISAGREE EICAS CAUTION ENG REF A I DISAG LIGHT Master Caution Check ice protection system selection against takeoff data entered EN...

Page 486: ...Associated FADEC RESET If FADEC alternates automatically Avoid quick movements of the associated Thrust Lever NOTE Thrust Lever movements may cause surge or an uncommanded engine shutdown If the asso...

Page 487: ...ted FADEC RESET If Thrust Lever command is not available Associated FADEC ALTN Check on EICAS that FADEC in control has changed If thrust lever still does not respond thrust can be partially controlle...

Page 488: ...ocedure AS REQUIRED TCAS TA ONLY FADEC NOT DISPATCHABLE EICAS CAUTION FADEC ID NO DISP LIGHT Master Caution Crew awareness ADC DATA FAIL EICAS ADVISORY E1 2 ADC DATA FAIL Confirm the failed side Assoc...

Page 489: ...VIBRATION WITHIN LIMITS CAUTION CONTINUOUS VIBRATION ABOVE LIMITS MAY DAMAGE THE ENGINE TCAS TA ONLY If vibration indication remains out of limits PRECAUTIONARY ENGINE SHUTDOWN Procedure ACCOMPLISH E...

Page 490: ...ITT N1 and N2 indications If engine is operative but the indications are lost proceed Associated FADEC RESET If engine indications are still not available Associated FADEC ALTN If engine indications a...

Page 491: ...OT OPEN THE SPEED BRAKE If one system can be recovered complete the appropriate procedure for one hydraulic system failure If both systems remain inoperative Quick Disconnect Button PRESS Both Electri...

Page 492: ...EICAS CAUTION HYD SYS 1 FAIL RUDDER SYS 1 INOP AIL SYS 1 INOP EICAS ADVISORY E1 HYD PUMP FAIL LIGHT Master Caution INDICATION Hydraulic pressure indication on MFD may be amber Check hydraulic systems...

Page 493: ...ve Inboard Spoiler Outboard Brakes LH Thrust Reverser Landing Gear Extension Steering and Nose Landing Gear Doors Retraction HYDRAULIC SYSTEM 2 FAILURE EICAS CAUTION HYD SYS 2 FAIL RUDDER SYS 2 INOP A...

Page 494: ...e Emergency Parking Brake will be available only with the accumulator charge HYDRAULIC SYSTEM OVERHEAT EICAS CAUTION HYD SYS 1 2 OVHT LIGHT Master Caution Associated Engine Hydraulic Pump SHUTOFF Asso...

Page 495: ...e if the Hydraulic System 2 is affected HYDRAULIC SYSTEM 1 2 FAILURE Procedure AS REQUIRED HYDRAULIC ENGINE PUMP FAILURE EICAS ADVISORY E1 2 HYD PUMP FAIL Monitor associated hydraulic system Refer to...

Page 496: ...ABNORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 48 Page 6 Code 03 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 497: ...presented Downlock Release Button PRESS Landing Gear Lever UP Landing gear lever will be released permitting gear retraction ABNORMAL LANDING GEAR EXTENSION CONDITION Landing gear has not extended by...

Page 498: ...MPLISH PARTIAL OR GEAR UP LANDING EICAS WARNING LG LEVER DISAGREE LIGHT Master Warning CONDITION Airplane committed to land with gear up or in transit EICAS Indication Landing gear indication may pres...

Page 499: ...ended that a gear up landing should be considered Landing Briefing PERFORM Just before touchdown Cabin ANNOUNCE IMPACT Apply thrust reversers if available at touchdown Ground spoilers thrust reversers...

Page 500: ...r anti ice failure messages appear leave and avoid icing conditions After exiting icing conditions proceed as follows Maximum Bank Angle 30 Minimum Airspeed for Flaps up or 9 190 KIAS Landing Configur...

Page 501: ...possible Airspeed BELOW 200 KIAS Retract gear when brakes temperature is in the green range If MFD is not available retract gear after message is removed Airspeed AS REQUIRED When on ground park the a...

Page 502: ...rakes is inoperative apply brakes normally through the pedals If both pair of brakes are inoperative EMERGENCY BRAKING TECHNIQUE Procedure ACCOMPLISH In any case Landing configuration Flaps 45 Airspee...

Page 503: ...rst airplane reaction Use the parking brake light as a reference for brake application Modulate brake application until the airplane achieves the desired deceleration In case of airplane skidding rele...

Page 504: ...tection This may cause the nose wheel to be steered up to its limit and may exacerbate the swerving effect NOSE LANDING GEAR DOOR OPEN CONDITION Noise increase due to nose landing gear doors open Airs...

Page 505: ...cessary turn on one rudder system at a time to identify the failed system Prepare to overcome the yaw generated by the failed system If both systems remains inoperative Expect greater rudder pedals fo...

Page 506: ...turbulence or crosswind Perform a long final approach Approach and landing configuration Landing Gear DOWN Flaps 22 Airspeed VREF 45 30 KIAS CAUTION TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE...

Page 507: ...Affected Rudder System OFF If RUDDER SYS 1 2 INOP message is displayed Rudder System 2 OFF If RUDDER SYS 1 2 INOP message is still displayed Rudder System 1 OFF CAUTION IF THE MESSAGE IS PRESENTED FO...

Page 508: ...KIAS 9 to 21 VREF 45 10 KIAS 22 to 44 VREF 45 5 KIAS 45 VREF 45 CAUTION TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 45 BY 1 65 WHEN LANDING W...

Page 509: ...RSPEED 0 to 8 VREF 45 30 KIAS 9 to 21 VREF 45 10 KIAS 22 to 44 VREF 45 5 KIAS 45 VREF 45 CAUTION TO DETERMINE THE MINIMUM SUITABLE LANDING DISTANCE MULTIPLY THE UNFACTORED LANDING DISTANCE FOR FLAPS 4...

Page 510: ...ubsequent jamming occurs Affected Surface Disconnection Handle PULL If the failure persists control the airplane using rudder trims aileron and asymmetric thrust as required Avoid landing at airports...

Page 511: ...perly although its pictorial indicates normal condition Rudder System 2 OFF If the failure persists Rudder System 1 OFF RUDDER MECHANICAL REVERSION MODE Procedure APPLY ASYMMETRIC RUDDER OPERATION CON...

Page 512: ...EICAS CAUTION PTRIM CPT SW FAIL PTRIM F O SW FAIL PTRIM BKP SW FAIL On ground Deenergize the airplane and energize it again In flight Use another serviceable switch STIFFENED ELEVATOR EICAS WARNING AU...

Page 513: ...dicates low temperature white range Associated Thrust Lever ADVANCE Adjust associated Thrust Lever until the message disappears or until the pointer of the failed side reaches the green range or the r...

Page 514: ...GINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE BLEED VALVE FAILURE EICAS Caution BLD 1 2 VLV FAIL LIGHT Master Caution If BLD 2 VLV CLSD message is also displayed on the EICAS Crossbleed...

Page 515: ...E Procedure ACCOMPLISH APU BLEED VALVE FAIL EICAS Caution APU BLD VLV FAIL LIGHT Master Caution If valve failed closed Engine Bleed AS REQUIRED If valve failed open and a duct leak exists OPEN annunci...

Page 516: ...eness RAM AIR VALVE FAILURE EICAS Caution RAM AIR VLV FAIL LIGHT Master Caution Air Conditioning System MONITOR If the PACK 1 2 OVLD or PACK 1 2 OVHT caution message appears Associated Pack OFF Altitu...

Page 517: ...eset report to the maintenance personnel If the message remains on Associated Temperature Mode Selector MANUAL 12 O CLOCK Associated Pack OFF Wait 3 minutes Associated Pack ON If the message still rem...

Page 518: ...ociated Pack ON If message remains Associated Temperature Mode Selector MANUAL FULL COLD Associated Pack OFF Wait 3 minutes Associated Pack ON If the message still remains Associated Pack OFF Altitude...

Page 519: ...Altitude MAX 25000 ft MINIMUM MEA WARNING IF IN ICING CONDITIONS REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE If both packs have been shutoff Altitude MEA OR 10000 f...

Page 520: ...al cabin altitude amber or red may be presented Erratic cabin rate fluctuations may be presented Pressurization Manual Controller 11 O CLOCK POSITION NOTE At least one bleed engines or APU must be ope...

Page 521: ...elow 10000 ft according to the table below AIRPLANE ALTITUDE ft CABIN ALTITUDE ft DIFFERENTIAL PRESSURE psi 10000 300 4 4 11000 500 4 7 12000 700 5 0 13000 900 5 2 14000 1100 5 5 15000 1300 5 7 16000...

Page 522: ...AWC Flight Management System FMS Attitude and Heading Reference System AHRS Passenger Address Integrated Navigation Unit INU Inverters Dimmers Backup Battery It is recommended to turn off the systems...

Page 523: ...t phase of flight SYSTEM POWER OFF CONTROL FMS For Honeywell FMS For FMS 1 CMPTR 1 CB For FMS 2 CMPTR 2 CB For Universal FMS FMS 1 CB FMS 2 CB NOTE Some airplanes may not be equipped with dual FMS Aur...

Page 524: ...ABNORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 56 Page 12 Code 03 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 525: ...Icing Button CYCLE If failure persists Wing Anti Icing Button OFF Avoid or exit icing conditions After exiting icing conditions Ice Detection Override Knob AUTO Maximum Bank Angle 30 Minimum Airspeed...

Page 526: ...s Ice Detection Override Knob AUTO Maximum Bank Angle 30 Minimum Airspeed for Flaps up or 9 190 KIAS Landing configuration Flaps 22 Airspeed VREF 45 15 KIAS CAUTION TO DETERMINE THE MINIMUM SUITABLE L...

Page 527: ...rride Knob AUTO NOTE Ice Detection Override Knob must be set to ALL for at least 2 minutes after exiting icing conditions or after ICE CONDITION advisory message has disappeared In such condition caut...

Page 528: ...and AE3007A or AE3007A1 1 engines Post Mod SB 145 73 0010 below 9700 ft TAT above 19 C at sea level decreasing linearly to 5 C at 9700 ft and the remaining engine is at T O 1 mode For AE3007A1P or AE...

Page 529: ...L EICAS CAUTION ICE DET 1 2 FAIL or ICE DETECTORS FAIL LIGHT Master Caution Use visual cues ice accretion on windshield and windshield wipers and temperature criteria to determine whether icing condit...

Page 530: ...de icing is required If there is no clear ice on the wing surface disregard the message CLEAR ICE DETECTION SYSTEM FAILURE APPLICABLE TO EMB 145XR MODEL EICAS CAUTION CLR I INOP 1 2 LIGHT Master Caut...

Page 531: ...found If the Pitot 3 is the affected one standby instruments and pressurization system may be affected If necessary ADC Button Reversionary Panel PRESS AOA SENSOR HEATING FAILURE EICAS CAUTION AOA 1 2...

Page 532: ...ABNORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 57 Page 8 Code 03 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 533: ...f oxygen leakage through the crew mask mask hose flow indicator blinker or oxygen line No Smoking ON If oxygen leakage is verified in the crew mask mask hose or flow indicator Stowage Box Doors CLOSE...

Page 534: ...ABNORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 58 Page 2 Code 03 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 535: ...SS If cross side AHRS is not available Maintain wings level and constant airspeed until AHRS 1 2 ALN message is no longer displayed and attitude is recovered approximately 20 seconds CAUTION ATTITUDE...

Page 536: ...PRESENT POSITION EICAS ADVISORY AHRS 1 2 NO PPOS Enter Present Position AHRS ON BATTERY EICAS ADVISORY AHRS 1 2 ON BATT Associated AHRS will operate for 40 minutes AHRS OVERHEAT EICAS CAUTION AHRS 1 2...

Page 537: ...Do not takeoff DAU FAILURE EICAS CAUTION DAU 1 2 A FAIL with Master Caution Light or EICAS ADVISORY DAU 1 2 B FAIL If on ground do not takeoff Confirm the failed side and channel For DAU 1 A FAIL cau...

Page 538: ...irport NOTE If both channels of DAU 1 have failed the messages and indications associated with the following systems will not be available All messages and indications Oxygen Steering Pressurization L...

Page 539: ...takeoff temperature hydraulic pressure oxygen pressure Warning all warning messages if any DAU REVERSION EICAS ADVISORY DAU 1 2 REVERSION If the reversionary condition is not required press the assoc...

Page 540: ...lay In this case it will be shut down automatically Use reversionary capabilities DISPLAY OVERHEAT EICAS ADVISORY DU 1 2 3 4 5 OVHT An overheat condition may arise in the associated display In this ca...

Page 541: ...installed EGPWS TERRAIN SYS OVRD Button PRESS The Terrain Awareness Alerting and Display functions on MFD will be inhibited This will not affect the basic GPWS functions modes 1 to 7 If the FMS is re...

Page 542: ...MODE Abnormal Procedure Accomplish In case of GPS fail GPS FAILED Scratchpad Message for single GPS or GPS 1 FAILED and GPS 2 FAILED Scratchpad Messages for dual GPS and EGPWS is installed EGPWS TERR...

Page 543: ...1 MFD 1 and EICAS SG 1 Button PRESS NOTE In case of IC 1 failure the PIT TRIM 1 2 INOP message may not be available If IC 2 failed loss of MFD 2 and PFD 2 SG 2 Button PRESS IC FAN FAILURE EICAS ADVISO...

Page 544: ...PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 59 Page 8B Code 03 REVISION 40 AOM 145 1114 CONTINUED FROM PREVIOUS PAGE SG 2 Button PRESS If smoke persists ELECTRICAL SYSTEM FAILURE OR SMOKE Procedure AC...

Page 545: ...ate source of navigation for approach guidance IRS ALIGNMENT EICAS ADVISORY IRS 1 2 ALN IRU Mode Select Switch CHECK NAV This message is only presented during alignment phase or while the IRU mode sel...

Page 546: ...ator lights extinguished IRU Mode Select Switch NAV In flight Reversionary Panel IRS Button PRESS If cross side IRU is not available IRU Mode Select Switch ATT Maintain wings level and constant airspe...

Page 547: ...age is presented or inertial data ceases to be transmitted by IRU Associated IRS Reversionary Button PRESS Affected IRU Mode Select Switch OFF NOTE The Autopilot is not available If IRU is OFF the air...

Page 548: ...nt Enter latitude Check and reenter latitude Allow additional time for alignment Flashes Select the remaining IRU by pressing the IRS Button on the associated reversionary panel If necessary set mode...

Page 549: ...ot takeoff The IRU operates on backup DC power and will operate for 30 minutes BATT FAIL Do not takeoff NO AIR Do not takeoff Operate IRU until completion of flight If fault annunciator is ON or inert...

Page 550: ...TAL LOSS OF DISPLAY INFORMATION EXIT OR AVOID ICING CONDITIONS NOTE For EMB 145 XR model if one ADC fails indicated by a X red over the IAS and altitude tapes and a VS red annunciation displayed in th...

Page 551: ...y panel PFD or EICAS Blank or X red Use the MFD Knob to present the required information on MFD RA amber Compare both Radio Altimeter indications If required consider only the lower altitude indicatio...

Page 552: ...ation Standby Attitude Instrument Maintain a straight and leveled flight using the primary indication source Wait 3 minutes If error persists cage the instrument and wait 5 min RADIO ALTIMETER FAIL EI...

Page 553: ...RMLY Quick Disconnect Button PRESS Pitch Trim AS REQUIRED Trim the airplane Autopilot AS REQUIRED FD LATERAL MODE FAILURE EICAS CAUTION LATERAL MODE OFF LIGHT Master Caution The Flight Director has be...

Page 554: ...ll be presented if the crew turns the Flight Director off In this case the message must be disregarded AILERON OUT OF TRIM EICAS CAUTION AP AIL MISTRIM LIGHT Master Caution CONDITION Autopilot is enga...

Page 555: ...nsists in a smooth and slow airplane attitude change due to an autopilot system malfunction It may be recognized if one of the following symptoms occurs during approach Unusual glide slope small devia...

Page 556: ...rocedure PERFORM AS REQUIRED Consider the possibility of continuing and performing the landing if under visual conditions and the airplane position and attitude assure a safe landing For EMB 135 and E...

Page 557: ...AL WARN FAIL amber RAD ALT FAIL cyan for airplanes Post Mod SB 145 31 0020 or with an equivalent modification factory incorporated RA amber GS red or amber LOC red or amber ILS amber ATT FAIL red ATT...

Page 558: ...00 ft Radio Altitude Discontinue the approach On both cases perform a normal MISSED APPROACH Procedure unless the approach is continued under visual conditions and the airplane position and attitude a...

Page 559: ...must be used APPROACH WARNING COMBINER Message APCH WARN MISSED APPROACH Procedure PERFORM A MISSED APPROACH procedure must be performed unless the approach is continued under visual conditions and t...

Page 560: ...ABNORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL INTENTIONALLY BLANK AOM 145 1114 1 03 66 Page 2 Code 01 REVISION 40...

Page 561: ...IMUM 250 KIAS Smoke Goggle DON In case both windshields are impaired Cabin below 10000 ft DEPRESSURIZE Airspeed MAX 140 KIAS MINIMUM VREF Make sure there are no loose objects in the cockpit Direct Vis...

Page 562: ...ACFT S N Route From Altitude ft Date of incident Flight no To Airspeed kt Flight phase Approach Climb Level Flight Other Weather Cloud type Cover Ceiling ft Top at ft OAT C Rain Sleet Hail Snow None...

Page 563: ...afe configuration and VREF for approach and landing The use of a greater VREF will cause the landing distance to increase Against engine PRECAUTIONARY ENGINE SHUTDOWN Procedure if necessary APPLY Land...

Page 564: ...ouchdown Rate of descent LESS THAN 300 ft MIN OVERWEIGHT LANDING Before touchdown Rate of Descent MAXIMUM 300 FT MIN Touch smoothly the runway surface Reduce the engine thrust only after the touchdown...

Page 565: ...utopilot Yaw Damper DISENGAGE Both Flight Directors OFF If speed indication on both PFD is below 135 kt Rudder Shutoff Sys 1 PUSH OUT Avoid using the speed brake Altitude Thrust ADJUST Maintain airpla...

Page 566: ...2100 1700 Pitch deg 5 5 5 4 20000 0 56 M V S ft min 2600 2000 1600 1200 Pitch deg 6 5 5 5 30000 0 56 M V S ft min 2000 1400 1100 700 Pitch deg 6 6 6 6 34000 0 56 M V S ft min 1700 1200 900 400 CRUISE...

Page 567: ...240 KIAS V S ft min 1800 1700 1600 1600 Pitch deg 3 2 2 1 10000 240 KIAS V S ft min 2200 2000 1900 1800 Pitch deg 3 2 1 1 20000 240 KIAS V S ft min 2300 2200 2100 2000 Pitch deg 2 2 1 0 30000 240 KIAS...

Page 568: ...for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 7 0 VREF45 30 N1 48 5 52 3 55 8 59 1 Pitch deg 7 8 8 8 9 VREF45 15 N1 51 0 54 9 58 5 61 6 Final Approach...

Page 569: ...V S ft min 2600 2100 1700 1300 Pitch deg 4 3 3 3 20000 0 56 M V S ft min 1600 1100 800 600 Pitch deg 4 4 4 4 30000 0 56 M V S ft min 900 500 300 100 Pitch deg 4 4 5 34000 0 56 M V S ft min 800 400 200...

Page 570: ...240 KIAS V S ft min 1000 1000 1000 1000 Pitch deg 1 1 0 0 10000 240 KIAS V S ft min 1300 1200 1200 1200 Pitch deg 1 1 0 0 20000 240 KIAS V S ft min 1400 1400 1400 1400 Pitch deg 1 0 0 1 30000 240 KIAS...

Page 571: ...for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 7 0 VREF45 30 N1 48 6 52 3 55 7 61 9 Pitch deg 7 8 8 8 9 VREF45 15 N1 51 7 54 9 58 5 64 1 Final Approach...

Page 572: ...ft min 3800 3100 2700 2200 Pitch deg 7 6 6 5 20000 0 56 M V S ft min 3500 2800 2300 1800 Pitch deg 7 6 6 6 30000 0 56 M V S ft min 2700 2000 1600 1200 Pitch deg 7 7 7 7 37000 0 56 M V S ft min 1800 13...

Page 573: ...240 KIAS V S ft min 1800 1700 1600 1600 Pitch deg 3 2 2 1 10000 240 KIAS V S ft min 2100 1900 1800 1800 Pitch deg 2 2 1 1 20000 240 KIAS V S ft min 2200 2100 2000 1900 Pitch deg 2 2 1 0 30000 240 KIA...

Page 574: ...for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 7 0 VREF45 30 N1 48 9 52 5 55 7 58 8 Pitch deg 7 8 8 8 9 VREF45 15 N1 51 4 55 1 58 2 61 3 Final Approac...

Page 575: ...ft min 3500 2800 2400 1900 Pitch deg 6 5 5 5 20000 0 56 M V S ft min 3000 2300 1900 1500 Pitch deg 6 5 5 5 30000 0 56 M V S ft min 2000 1400 1100 700 Pitch deg 6 6 6 6 37000 0 56 M V S ft min 1200 70...

Page 576: ...0 240 KIAS V S ft min 900 900 900 900 Pitch deg 1 1 0 0 10000 240 KIAS V S ft min 1200 1200 1200 1200 Pitch deg 1 0 0 0 20000 240 KIAS V S ft min 1300 1300 1300 1300 Pitch deg 1 0 0 1 30000 240 KIAS...

Page 577: ...for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 7 0 VREF45 30 N1 48 9 52 5 55 7 61 3 Pitch deg 7 8 8 8 9 VREF45 15 N1 51 5 55 1 58 3 63 9 Final Approac...

Page 578: ...0 1900 Pitch deg 7 6 6 5 5 20000 0 56 M V S ft min 3500 2800 2300 1800 1500 Pitch deg 7 7 7 7 7 30000 0 56 M V S ft min 2700 2000 1600 1200 900 Pitch deg 7 7 7 8 8 37000 0 56 M V S ft min 1800 1300 90...

Page 579: ...t min 1800 1700 1600 1500 1500 Pitch deg 3 2 1 1 0 10000 240 KIAS V S ft min 2000 1900 1800 1700 1700 Pitch deg 2 2 1 1 0 20000 240 KIAS V S ft min 2200 2000 2000 1900 1900 Pitch deg 2 1 1 0 0 30000 2...

Page 580: ...for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 8 0 VREF45 30 N1 48 9 52 5 55 7 58 8 Pitch deg 7 7 7 8 9 VREF45 15 N1 51 5 55 2 58 4 61 6 Final Approac...

Page 581: ...1900 1600 Pitch deg 6 5 5 5 5 20000 0 56 M V S ft min 3000 2300 1900 1500 1200 Pitch deg 6 6 6 6 6 30000 0 56 M V S ft min 2000 1400 1100 700 400 Pitch deg 6 6 7 7 37000 0 56 M V S ft min 1200 700 40...

Page 582: ...min 900 900 900 900 900 Pitch deg 1 0 0 0 1 10000 240 KIAS V S ft min 1100 1100 1100 1100 1200 Pitch deg 1 0 0 0 1 20000 240 KIAS V S ft min 1300 1300 1300 1300 1300 Pitch deg 0 0 0 1 1 30000 240 KIAS...

Page 583: ...for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 7 0 VREF45 30 N1 48 9 52 5 55 7 61 3 Pitch deg 7 8 8 8 9 VREF45 15 N1 52 1 55 2 58 4 64 2 Final Approac...

Page 584: ...0 1700 1400 Pitch deg 6 5 5 5 5 20000 0 56 M V S ft min 2900 2300 1800 1400 1100 Pitch deg 6 6 6 6 6 30000 0 56 M V S ft min 2200 1600 1200 800 500 Pitch deg 7 7 7 7 37000 0 56 M V S ft min 1400 900 6...

Page 585: ...1800 1700 1600 1500 1500 Pitch deg 3 2 2 1 1 10000 240 KIAS V S ft min 2100 2000 1900 1800 1800 Pitch deg 2 2 1 1 0 20000 240 KIAS V S ft min 2300 2200 2100 2000 2000 Pitch deg 2 2 1 1 0 30000 240 KI...

Page 586: ...for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 7 0 VREF45 30 N1 48 2 52 2 56 0 59 0 Pitch deg 7 7 7 8 9 VREF45 15 N1 51 2 55 2 58 7 61 7 Final Approach...

Page 587: ...deg 7 7 6 6 6 10000 240 KIAS V S ft min 2800 2300 1900 1500 1200 Pitch deg 4 3 3 3 3 20000 0 56 M V S ft min 1600 1100 800 600 300 Pitch deg 4 4 4 30000 0 56 M V S ft min 700 300 100 Pitch deg 5 5 37...

Page 588: ...1800 1700 1600 1500 1500 Pitch deg 1 1 0 0 0 10000 240 KIAS V S ft min 1300 1300 1200 1200 1200 Pitch deg 1 0 0 0 1 20000 240 KIAS V S ft min 1400 1400 1400 1400 1400 Pitch deg 1 0 0 1 1 30000 240 KIA...

Page 589: ...or Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 8 0 VREF45 30 N1 48 2 52 2 56 0 61 5 Pitch deg 7 7 7 8 9 VREF45 15 N1 51 9 55 1 58 7 64 1 Final Approach...

Page 590: ...1900 1600 Pitch deg 6 5 5 5 5 20000 0 56 M V S ft min 3000 2400 2000 1500 1200 Pitch deg 6 6 6 6 6 30000 0 56 M V S ft min 2300 1700 1300 900 600 Pitch deg 7 7 7 7 37000 0 56 M V S ft min 1500 1000 70...

Page 591: ...n 1800 1700 1600 1500 1500 Pitch deg 3 2 2 1 1 10000 240 KIAS V S ft min 2100 2000 1900 1800 1800 Pitch deg 2 2 1 1 0 20000 240 KIAS V S ft min 2300 2100 2000 2000 1900 Pitch deg 2 2 1 0 0 30000 240 K...

Page 592: ...for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 7 0 VREF45 30 N1 48 0 51 8 55 4 58 7 Pitch deg 7 7 7 8 9 VREF45 15 N1 50 9 55 0 58 4 61 6 Final Approac...

Page 593: ...2600 2200 1800 1500 Pitch deg 4 4 3 3 3 20000 0 56 M V S ft min 1700 1200 900 700 400 Pitch deg 4 4 4 4 30000 0 56 M V S ft min 2000 1400 1100 700 Pitch deg 5 5 37000 0 56 M V S ft min 500 100 CRUISE...

Page 594: ...n 1800 1700 1600 1500 1500 Pitch deg 1 1 0 0 1 10000 240 KIAS V S ft min 1200 1200 1200 1200 1200 Pitch deg 1 0 0 0 1 20000 240 KIAS V S ft min 1400 1400 1400 1400 1400 Pitch deg 1 0 0 1 1 30000 240 K...

Page 595: ...for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 8 0 VREF45 30 N1 48 0 51 8 55 4 61 5 Pitch deg 7 7 7 8 9 VREF45 15 N1 51 6 55 0 58 4 64 2 Final Approac...

Page 596: ...g 7 6 6 5 5 5 20000 0 56 M V S ft min 3500 2800 2300 1800 1500 1200 Pitch deg 7 7 7 8 7 7 30000 0 56 M V S ft min 2700 2000 1600 1200 900 600 Pitch deg 7 7 8 8 8 37000 0 56 M V S ft min 1800 1300 900...

Page 597: ...0 1500 Pitch deg 3 2 1 1 0 0 10000 240 KIAS V S ft min 2000 1900 1800 1800 1700 1700 Pitch deg 2 2 1 1 0 0 20000 240 KIAS V S ft min 2200 2100 2000 1900 1900 1900 Pitch deg 2 2 1 0 0 1 30000 240 KIAS...

Page 598: ...1 for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 8 0 VREF45 30 N1 48 9 52 5 55 7 58 8 Pitch deg 7 7 7 8 9 VREF45 15 N1 51 6 55 3 58 6 61 7 Final Approa...

Page 599: ...h deg 6 5 5 5 5 5 20000 0 56 M V S ft min 3000 2300 1900 1500 1200 900 Pitch deg 6 6 6 6 6 6 30000 0 56 M V S ft min 2000 1400 1100 700 400 200 Pitch deg 6 6 7 7 37000 0 56 M V S ft min 1200 700 400 0...

Page 600: ...000 Pitch deg 1 0 0 0 1 1 10000 240 KIAS V S ft min 1200 1200 1200 1200 1200 1200 Pitch deg 1 0 0 0 1 1 20000 240 KIAS V S ft min 1300 1300 1300 1300 1300 1400 Pitch deg 0 0 0 1 1 2 30000 240 KIAS V S...

Page 601: ...1 for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 8 0 VREF45 30 N1 48 9 52 5 55 7 61 3 Pitch deg 7 7 7 8 9 VREF45 15 N1 52 3 55 3 58 6 64 3 Final Approa...

Page 602: ...1500 Pitch deg 4 4 4 4 4 4 20000 0 56 M V S ft min 1800 1400 1200 1100 900 800 Pitch deg 6 6 6 6 6 6 30000 0 56 M V S ft min 1900 1400 1200 900 600 300 Pitch deg 6 7 7 7 37000 0 56 M V S ft min 1400 9...

Page 603: ...0 2000 Pitch deg 5 4 3 2 2 1 10000 240 KIAS V S ft min 3000 3000 2800 2500 2300 2100 Pitch deg 4 3 3 2 1 1 20000 240 KIAS V S ft min 3000 3000 2900 2700 2500 2400 Pitch deg 3 2 2 1 1 0 30000 240 KIAS...

Page 604: ...a 5000 ft N1 for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 8 0 VREF45 30 N1 51 4 54 8 57 9 60 9 Pitch deg 7 7 8 8 9 VREF45 15 N1 49 3 52 8 56 0 58 8 F...

Page 605: ...00 1400 1200 Pitch deg 3 3 3 3 3 4 20000 0 56 M V S ft min 900 800 700 600 400 300 Pitch deg 4 4 5 5 5 0 30000 0 56 M V S ft min 900 700 500 300 0 0 Pitch deg 5 5 0 0 37000 0 56 M V S ft min 500 100 0...

Page 606: ...1500 Pitch deg 4 3 2 1 1 0 10000 240 KIAS V S ft min 2700 2300 2100 1900 1800 1700 Pitch deg 3 2 2 1 0 0 20000 240 KIAS V S ft min 2900 2500 2200 2100 2000 1900 Pitch deg 3 2 1 0 0 1 30000 240 KIAS V...

Page 607: ...a 5000 ft N1 for Level Flight WEIGHT lb Flap position VREF INCREMENT 30000 35000 40000 45000 Pitch deg 7 7 7 8 0 VREF45 30 N1 51 4 54 8 57 9 63 4 Pitch deg 7 7 8 8 9 VREF45 15 N1 49 9 52 8 56 0 61 2 F...

Page 608: ...ABNORMAL PROCEDURES AIRPLANE OPERATIONS MANUAL 1 03 70 Page 48 Code 03 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 609: ...AIRPLANE OPERATIONS MANUAL EMERGENCY PROFILES SEPTEMBER 29 2000 1 03 95 Page 1 Code 03 EMERGENCY PROFILES...

Page 610: ...EMERGENCY PROFILES AIRPLANE OPERATIONS MANUAL 1 03 95 Page 2 Code 03 SEPTEMBER 29 2000...

Page 611: ...AIRPLANE OPERATIONS MANUAL EMERGENCY PROFILES SEPTEMBER 29 2000 1 03 95 Page 3 Code 03...

Page 612: ...EMERGENCY PROFILES AIRPLANE OPERATIONS MANUAL 1 03 95 Page 4 Code 03 APRIL 28 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 613: ...AIRPLANE OPERATIONS MANUAL ABNORMAL PROFILES REVISION 24 1 03 97 Page 1 Code 01 ABNORMAL PROFILES...

Page 614: ...ABNORMAL PROFILES AIRPLANE OPERATIONS MANUAL 1 03 97 Page 2 Code 01 REVISION 25...

Page 615: ...AIRPLANE OPERATIONS MANUAL ABNORMAL PROFILES DECEMBER 20 2002 1 03 97 Page 3 Code 01...

Page 616: ...ABNORMAL PROFILES AIRPLANE OPERATIONS MANUAL 1 03 97 Page 4 Code 01 DECEMBER 20 2002...

Page 617: ...ntroduction 1 04 00 Noise Levels 1 04 03 Wind and Altitude Conversion 1 04 05 Thrust Setting Tables 1 04 10 Takeoff 1 04 15 Supplementary Takeoff Information 1 04 20 Approach 1 04 25 Landing 1 04 30 L...

Page 618: ...13 INTRODUCTION This section presents takeoff approach and landing performance information For determination of the takeoff and landing limiting weights the performance data as presented in the approv...

Page 619: ...lls Royce AE3007A AE3007A1 AE3007A1 1 AE3007A1P or AE3007A1E engines or EMB 135 equipped with two Rolls Royce AE3007A3 or AE3007A1 3 engines at the MTOW Maximum Takeoff Weight related to each model V2...

Page 620: ...tual 86 9 81 2 91 6 ERJ 140 ER EMB 135 KE model Actual 84 3 79 7 92 4 ERJ 140 LR EMB 135 KL model Actual 84 2 80 4 92 4 EMB 135 ER model Actual 84 4 4 78 6 4 92 3 EMB 135 LR model Actual 84 3 79 4 92...

Page 621: ...ped with an equivalent modification factory incorporated the actual noise level for Sideline condition is 85 0 EPNdB and for Takeoff condition is 80 5 EPNdB 6 For airplanes Post Mod SB 145 53 0066 or...

Page 622: ...PERFORMANCE AIRPLANE OPERATIONS MANUAL 1 04 03 Page 4 Code 01 REVISION 34 INTENTIONALLY BLANK...

Page 623: ...AIRPLANE OPERATIONS MANUAL PERFORMANCE DECEMBER 20 2002 1 04 05 Page 1 Code 01 WIND AND ALTITUDE CONVERSION...

Page 624: ...USE Enter the chart with the reported wind velocity and the relative angle to the runway to read the wind component parallel to the runway and the crosswind EXAMPLE Given Wind velocity 20 kt Wind dire...

Page 625: ...97 500 29 45 to 29 55 998 to 1001 400 29 56 to 29 66 1002 to 1004 300 29 67 to 29 76 1005 to 1008 200 29 77 to 29 87 1009 to 1012 100 29 88 to 29 97 1013 to 1015 0 29 98 to 30 08 1016 to 1019 100 30 0...

Page 626: ...641 23 77 805 6230 29 09 985 781 23 62 800 6394 28 94 980 921 23 48 795 6561 28 79 975 1062 23 33 790 6727 28 64 970 1202 23 18 785 6895 28 50 965 1344 23 03 780 7063 28 35 960 1486 22 89 775 7233 28...

Page 627: ...nditions of extremely cold temperature ICAO PANS OPS Vol I 3 5 4 5 2 AERODROME TEMP o C HEIGHT ABOVE THE ELEVATION OF THE ALTIMETER SETTING SOURCE feet ft 200 300 400 500 600 700 800 0 0 20 20 20 20 2...

Page 628: ...Height above airport elevation 800 ft Altimeter adjusted to airport QNH on ground altimeter reads 1500 ft Enter table with 800 ft and 20 o C and read 100 ft So when the airplane reaches the obstacle g...

Page 629: ...1 It is an engine rating lower than the takeoff thrust intended for engine life extension due to lower turbine temperatures It is also time limited to 5 minutes In case of engine failure the FADEC wi...

Page 630: ...82 8 83 7 84 6 85 4 86 2 87 1 87 9 5000 80 4 81 1 82 0 82 9 83 8 84 7 85 6 86 4 87 3 88 1 88 9 6000 80 9 81 7 82 6 83 5 84 4 85 2 86 1 87 0 87 8 88 7 89 5 7000 81 4 82 2 83 1 84 0 84 9 85 8 86 7 87 5...

Page 631: ...000 87 7 88 5 89 2 90 0 90 8 91 6 92 3 92 7 91 8 91 0 90 4 4000 88 7 89 5 90 3 91 1 91 9 92 7 93 2 93 1 91 8 91 0 90 7 5000 89 8 90 6 91 4 92 2 93 0 93 8 93 7 92 7 91 9 91 0 6000 90 3 91 2 92 0 92 8 9...

Page 632: ...0 79 8 80 6 81 5 82 3 83 1 83 9 84 7 5000 77 5 78 3 79 1 80 0 80 8 81 7 82 5 83 4 84 2 85 0 85 8 6000 78 0 78 7 79 6 80 5 81 3 82 2 83 0 83 9 84 7 85 5 86 3 7000 78 5 79 2 80 1 81 0 81 8 82 7 83 5 84...

Page 633: ...3000 84 3 85 1 85 9 86 6 87 4 88 1 88 9 89 2 88 4 87 8 87 3 4000 85 5 86 2 87 0 87 8 88 5 89 3 89 8 89 1 88 5 87 8 87 6 5000 86 6 87 4 88 2 88 9 89 7 90 3 90 2 89 1 88 5 87 9 6000 87 1 87 9 88 7 89 5...

Page 634: ...82 8 83 6 84 5 85 3 86 2 87 0 87 8 5000 80 4 81 1 82 0 82 9 83 8 84 6 85 5 86 4 87 2 88 0 88 9 6000 80 8 81 5 82 5 83 4 84 2 85 1 86 0 86 9 87 7 88 6 89 4 7000 81 3 82 0 82 9 83 8 84 7 85 6 86 5 87 4...

Page 635: ...3000 87 6 88 4 89 2 90 0 90 7 91 5 92 3 92 6 91 7 90 9 90 3 4000 88 6 89 5 90 3 91 0 91 8 92 6 93 1 93 0 91 8 91 0 90 6 5000 89 7 90 5 91 3 92 1 92 9 93 7 93 6 92 6 91 8 91 0 6000 90 2 91 0 91 9 92 7...

Page 636: ...82 7 83 6 84 4 85 3 86 1 87 0 87 8 5000 80 3 81 1 82 0 82 9 83 7 84 6 85 5 86 3 87 2 88 0 88 9 6000 80 7 81 5 82 4 83 3 84 2 85 1 85 9 86 8 87 6 88 5 89 3 7000 81 2 81 9 82 8 83 7 84 6 85 5 86 4 87 2...

Page 637: ...3000 87 5 88 3 89 1 89 9 90 7 91 4 92 2 92 5 91 6 90 8 90 1 4000 88 6 89 4 90 2 91 0 91 8 92 6 93 1 93 0 91 7 90 8 90 5 5000 89 7 90 5 91 3 92 1 92 9 93 7 93 6 92 5 91 7 90 9 6000 90 1 91 0 91 8 92 6...

Page 638: ...82 7 83 6 84 4 85 3 86 1 86 9 87 8 5000 80 4 81 1 82 0 82 9 83 8 84 6 85 5 86 3 87 2 88 0 88 9 6000 80 7 81 5 82 4 83 3 84 2 85 0 85 9 86 8 87 6 88 5 89 3 7000 81 1 81 8 82 8 83 7 84 5 85 4 86 3 87 2...

Page 639: ...3000 87 4 88 2 89 0 89 8 90 6 91 3 92 1 92 5 91 5 90 5 89 7 4000 88 6 89 4 90 2 91 0 91 7 92 5 93 1 92 9 91 5 90 6 90 2 5000 89 7 90 5 91 3 92 1 92 9 93 7 93 6 92 4 91 6 90 7 6000 90 1 91 0 91 7 92 6...

Page 640: ...86 0 86 8 87 7 88 5 89 4 14000 79 6 80 6 81 7 82 5 83 4 84 3 85 2 86 1 86 9 87 8 88 7 89 6 90 4 16000 80 6 81 5 82 7 83 4 84 4 85 3 86 2 87 1 88 0 88 9 89 7 90 6 91 5 18000 81 7 82 7 83 8 84 6 85 6 8...

Page 641: ...8 86 6 87 3 88 0 88 8 88 9 88 0 87 2 4000 85 7 86 5 87 3 88 1 88 8 89 6 90 1 89 4 88 8 88 1 87 9 6000 87 4 88 2 89 0 89 7 90 5 90 8 90 0 89 4 88 8 88 3 8000 88 4 89 2 90 0 90 8 91 3 90 6 90 0 89 3 88...

Page 642: ...86 0 86 9 87 7 88 6 89 4 14000 79 6 80 6 81 7 82 4 83 3 84 2 85 1 86 0 86 9 87 8 88 6 89 5 90 3 16000 80 4 81 3 82 5 83 2 84 2 85 1 86 0 86 9 87 8 88 6 89 5 90 4 91 2 18000 81 3 82 3 83 5 84 2 85 2 8...

Page 643: ...85 9 86 7 87 4 88 1 88 8 89 0 87 9 87 0 3000 84 7 85 5 86 3 87 0 87 8 88 5 89 3 89 7 88 8 88 0 87 3 4000 85 8 86 6 87 4 88 2 88 9 89 7 90 2 89 5 88 8 88 1 87 7 5000 87 0 87 7 88 5 89 3 90 1 90 7 90 6...

Page 644: ...86 1 86 9 87 8 88 6 89 5 14000 79 6 80 5 81 7 82 4 83 3 84 2 85 1 86 0 86 9 87 8 88 6 89 5 90 3 16000 80 2 81 2 82 3 83 1 84 0 84 9 85 8 86 7 87 6 88 5 89 3 90 2 91 1 18000 80 9 81 9 83 0 83 8 84 7 8...

Page 645: ...0 86 7 87 5 88 2 88 9 89 1 87 8 86 6 4000 86 0 86 7 87 5 88 3 89 0 89 8 90 2 89 6 88 9 88 0 87 6 6000 87 6 88 4 89 1 89 9 90 7 91 0 90 2 89 7 88 9 88 5 8000 88 5 89 4 90 1 90 9 91 4 90 7 90 2 89 6 89...

Page 646: ...6 6 87 4 88 3 89 1 88 7 89 5 89 5 5000 84 1 85 0 85 9 86 7 87 6 88 5 89 3 90 2 89 8 90 5 89 5 6000 84 6 85 5 86 4 87 3 88 2 89 0 89 9 90 7 90 3 90 1 89 1 7000 85 1 86 0 86 9 87 8 88 7 89 6 90 4 91 3 9...

Page 647: ...83 5 84 3 85 1 85 9 85 5 86 2 87 0 5000 81 1 82 0 82 9 83 7 84 5 85 4 86 2 87 0 86 6 87 4 88 1 6000 81 6 82 5 83 3 84 2 85 0 85 9 86 7 87 5 87 1 87 9 88 7 7000 82 1 83 0 83 8 84 7 85 5 86 4 87 2 88 0...

Page 648: ...6 5 87 4 88 2 89 0 88 6 89 5 89 8 5000 84 0 84 9 85 8 86 7 87 5 88 4 89 3 90 1 89 7 90 5 89 8 6000 84 5 85 4 86 3 87 2 88 1 88 9 89 8 90 6 90 2 90 5 89 5 7000 85 0 85 9 86 8 87 7 88 5 89 4 90 3 91 1 9...

Page 649: ...89 0 88 6 89 4 89 8 5000 83 1 84 0 84 9 85 8 86 7 87 5 88 4 89 2 90 1 89 7 90 5 89 9 6000 83 5 84 4 85 3 86 2 87 1 88 0 88 8 89 7 90 5 90 2 90 6 89 6 7000 83 9 84 9 85 8 86 7 87 5 88 4 89 3 90 2 91 0...

Page 650: ...6 5 87 3 88 1 89 0 88 6 89 4 89 8 5000 84 0 84 9 85 8 86 7 87 6 88 4 89 3 90 1 89 7 90 5 89 9 6000 84 4 85 3 86 2 87 1 88 0 88 8 89 7 90 5 90 1 90 7 89 7 7000 84 8 85 7 86 6 87 5 88 4 89 2 90 1 91 0 9...

Page 651: ...87 1 88 0 88 8 89 0 86 9 86 0 85 0 12000 84 5 85 4 86 3 87 2 88 0 88 9 88 8 88 0 86 0 85 2 84 4 14000 85 4 86 3 87 3 88 1 89 0 88 8 88 1 87 5 85 5 84 8 83 9 16000 86 4 87 3 88 3 89 2 89 1 88 5 87 9 8...

Page 652: ...87 2 88 1 88 9 89 6 87 4 86 4 85 4 12000 84 5 85 4 86 3 87 2 88 1 88 9 89 4 88 6 86 5 85 6 84 6 14000 85 4 86 3 87 2 88 1 89 0 89 2 88 5 87 8 85 7 84 9 84 0 16000 86 2 87 1 88 1 89 0 89 3 88 7 88 0 8...

Page 653: ...87 4 88 2 89 1 89 9 87 8 86 8 85 7 12000 84 6 85 5 86 4 87 3 88 1 89 0 89 9 89 1 86 9 85 9 84 9 14000 85 4 86 3 87 2 88 1 89 0 89 6 88 8 88 0 86 0 85 1 84 1 16000 86 1 87 0 87 9 88 8 89 4 88 8 88 1 8...

Page 654: ...PERFORMANCE EMB 145 A1 AIRPLANE OPERATIONS MANUAL 1 04 10 Page 26 Code 01 REVISION 27 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 655: ...as far as the appropriate Static Air Temperature Range b Enter the table with Airplane Brake Release Gross Weight and move right as far as the appropriate temperature column Read V1 VR and V2 If nece...

Page 656: ...32000 101 105 120 101 103 117 102 104 117 104 105 117 33000 103 106 121 103 105 119 104 106 119 106 107 119 34000 105 107 122 106 108 121 107 108 121 109 109 121 35000 107 109 123 108 110 122 109 110...

Page 657: ...116 95 105 114 93 102 110 94 100 108 33000 97 107 116 96 105 113 95 103 110 96 102 109 34000 98 107 116 97 105 113 97 104 111 99 103 110 35000 99 107 116 98 105 114 98 105 112 102 105 111 36000 100 1...

Page 658: ...104 119 100 103 118 101 103 117 103 104 117 33000 103 106 121 103 105 119 104 105 119 105 107 119 34000 105 107 122 105 107 121 106 108 121 108 109 121 35000 107 109 123 108 109 123 109 110 122 110 1...

Page 659: ...V2 15 KIAS Takeoff with flaps 22 Flaps 22 to 9 V2 5 KIAS Flaps 9 to UP V2 25 KIAS FINAL SEGMENT SPEED WEIGHT lb VFS KIAS 28000 136 29000 139 30000 141 31000 142 32000 145 33000 147 34000 150 35000 152...

Page 660: ...IRPLANE OPERATIONS MANUAL 1 04 15 Page 6 Code 02 REVISION 26 PITCH TRIM SETTING FOR TAKEOFF CG POSITION LESS THAN OR EQUAL TO 27 5 27 6 UP TO 32 5 32 6 UP TO 36 5 36 6 UP TO 41 5 ABOVE OR EQUAL TO 41...

Page 661: ...t for Anti Ice ON and Flaps 22 are also provided below each table GRADIENTS FOR TAKEOFF THRUST AND FLAPS UP The gradients were obtained for a speed equal to 200 KIAS The thrust rating was T O 1 with A...

Page 662: ...20 48 18 97 17 60 16 35 15 22 14 20 20 33 88 31 06 28 51 26 16 24 05 22 17 20 49 18 98 17 60 16 36 15 23 14 20 10 33 83 31 01 28 46 26 12 24 01 22 13 20 45 18 94 17 57 16 32 15 20 14 17 0 33 73 30 92...

Page 663: ...8 18 13 16 74 15 48 14 33 13 30 12 36 20 30 79 28 06 25 57 23 36 21 42 19 70 18 15 16 76 15 50 14 36 13 33 12 39 10 30 79 28 06 25 57 23 35 21 41 19 69 18 14 16 75 15 49 14 35 13 31 12 38 0 30 71 27 9...

Page 664: ...8 16 07 14 72 13 50 12 40 11 40 10 50 9 69 20 25 53 23 03 20 84 18 92 17 25 15 76 14 42 13 22 12 13 11 15 10 26 9 45 30 22 01 19 75 17 78 16 06 14 55 13 21 12 01 10 93 9 96 9 08 ALTITUDE 13500 FT ISA...

Page 665: ...26 18 07 16 99 15 98 15 05 14 18 20 29 52 27 28 25 30 23 54 21 97 20 55 19 25 18 07 16 98 15 98 15 05 14 18 10 29 47 27 23 25 26 23 51 21 93 20 51 19 22 18 04 16 95 15 95 15 02 14 15 0 29 36 27 13 25...

Page 666: ...17 09 16 01 15 02 14 10 13 25 12 45 20 26 48 24 44 22 64 21 04 19 60 18 31 17 12 16 04 15 05 14 13 13 27 12 48 10 26 44 24 41 22 61 21 01 19 58 18 28 17 10 16 02 15 03 14 11 13 25 12 46 0 26 35 24 32...

Page 667: ...2 90 12 05 11 26 10 53 9 84 20 21 33 19 63 18 13 16 80 15 60 14 51 13 52 12 61 11 77 10 99 10 27 9 59 30 18 27 16 78 15 46 14 28 13 22 12 26 11 38 10 57 9 82 9 13 8 49 7 88 ALTITUDE 13500 FT ISA C WEI...

Page 668: ...00 36000 38000 40000 42000 44000 46000 48000 50000 30 19 62 18 11 16 78 15 60 14 53 13 58 12 71 11 91 11 18 10 50 9 88 9 16 20 19 63 18 12 16 79 15 61 14 55 13 59 12 72 11 92 11 19 10 51 9 89 9 17 10...

Page 669: ...0 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 30 15 68 14 43 13 33 12 35 11 47 10 67 9 94 9 28 8 67 8 10 7 57 6 97 20 15 72 14 47 13 36 12 38 11 49 10 69 9 97 9 30 8 69 8 12 7 59...

Page 670: ...ISA C WEIGHT LB 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 30 6 75 6 13 5 58 5 10 4 66 4 26 3 90 3 57 3 27 2 99 2 73 2 27 20 6 77 6 15 5 60 5 11 4 67 4 28 3 92 3 59 3 28...

Page 671: ...39 4 86 4 39 3 96 3 59 3 24 2 93 2 64 2 38 2 14 1 91 1 50 0 5 37 4 83 4 36 3 94 3 57 3 22 2 91 2 63 2 36 2 12 1 89 1 48 10 4 93 4 42 3 98 3 58 3 22 2 90 2 60 2 33 2 08 1 85 1 64 1 24 20 2 80 2 44 2 12...

Page 672: ...PERFORMANCE EMB 145 A1 FAA AIRPLANE OPERATIONS MANUAL 1 04 15 Page 18 Code 02 REVISION 28 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 673: ...clearance With the equivalent straight flight path the performance calculation must be done as usual as presented in the AFM OPERATIONAL LIMITATIONS Maximum bank angle All Engines Operative 25 o at V...

Page 674: ...d to still air equivalent distance as follows SAD GD TAS GS Where SAD still air equivalent distance GD actual ground distance TAS airplane true airspeed obtained from the radius of turns and speed con...

Page 675: ...x VW D trajectory displacement in the wind component direction t elapsed time in turning flight obtained from the Horizontal Distance and Time to Complete chart VW wind speed b2 Distance Flown Compen...

Page 676: ...ws the radius of turn and the true airspeed to be used on the turning flight path calculation as a function of the indicated airspeed V2 airport pressure altitude outside air temperature and the bank...

Page 677: ...ADIENT LOSS DUE TO A STEADY TURN ONE ENGINE INOPERATIVE TAKEOFF FLAPS 9 0 0 0 2 0 4 0 6 0 8 1 0 1 2 1 4 1 6 1 8 2 0 2 2 2 4 2 6 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 BANK ANGLE deg GRADIENT LOSS...

Page 678: ...ANK ANGLE deg GRADIENT LOSS GRLOSS_TO MAY 07 2001 V KIAS 0 0 15 0 20 5 25 10 30 15 ALL ENGINES MODELS GRADIENT LOSS DUE TO A STEADY TURN ONE ENGINE INOPERATIVE TAKEOFF FLAPS 18 0 0 0 2 0 4 0 6 0 8 1 0...

Page 679: ...DIENT LOSS ALL ENGINES MODELS aom145001 AGO 21 1999 AIRPLANE OPERATIONS MANUAL PERFORMANCE EMB 145 LB GRADIENT LOSSDUETOASTEADYTURN ONEENGINEINOPERATIVE TAKEOFF FLAPS 22 0 0 0 1 0 2 0 3 0 4 0 5 0 6 0...

Page 680: ...PERFORMANCE EMB 145 LB AIRPLANE OPERATIONS MANUAL 1 04 20 Page 8 Code 02 REVISION 40 INTENTIONALLY BLANK AOM 145 1114...

Page 681: ...AIRPLANE OPERATIONS MANUAL PERFORMANCE EMB 145 LB AOM 145 1114 REVISION 40 1 04 20 Page 9 Code 02...

Page 682: ...PERFORMANCE AIRPLANE EMB 145 LB OPERATIONS MANUAL INTENTIONALLY BLANK AOM 145 1114 1 04 20 Page 10 Code 02 REVISION 40...

Page 683: ...AIRPLANE OPERATIONS MANUAL PERFORMANCE EMB 145 LB REVISION 40 1 04 20 Page 11 Code 02 AOM 145 1114...

Page 684: ...PERFORMANCE EMB 145 LB AIRPLANE OPERATIONS MANUAL INTENTIONALLY BLANK AOM 145 1114 1 04 20 Page 12 Code 02 REVISION 40...

Page 685: ...um C Low D Ultra low 3 Maximum tire pressure authorized for the pavement W High no limit X Medium up to 217 psi Y Low up to 145 psi Z Very low up to 73 psi 4 Pavement evaluation method T Technical eva...

Page 686: ...ode 02 REVISION 40 EMB 145ER ACN FLEXIBLE PAVEMENT 4 6 8 10 12 14 16 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 WEIGHT lb AIRCRAFT CLASSIFICATION NUMBER ACN D...

Page 687: ...20 Page 15 Code 02 EMB 145EU ACN FLEXIBLE PAVEMENT 4 6 8 10 12 14 16 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 WEIGHT lb AIRCRAFT CLASSIFICATION NUMBER ACN D...

Page 688: ...de 02 REVISION 40 AOM 145 1114 EMB 145EP MP ACN FLEXIBLE PAVEMENT 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 WEIGHT lb 4 6 8 10 12 14 16 AIRCRAFT CLASSIFICATIO...

Page 689: ...Page 17 Code 02 AOM 145 1114 EMB 145LR LU ACN FLEXIBLE PAVEMENT 2 4 6 8 10 12 14 16 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 WEIGHT lb AIRCRAFT CLASSIFICATION NUM...

Page 690: ...EVISION 40 AOM 145 1114 EMB 145ER ACN RIGID PAVEMENT 0 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 WEIGHT lb 4 6 8 10 12 14 16 2400 AIRCRAFT CLASSIFICATION NUMBER ACN...

Page 691: ...42000 44000 46000 48000 50000 WEIGHT lb AIRCRAFT CLASSIFICATION NUMBER ACN 145AOM004 JUN 23 1999 D K 20 MN m3 C K 40 MN m3 B K 80 MN m3 A K 150 MN m3 REVISION 40 1 04 20 Page 19 Code 02 EMB 145EU ACN...

Page 692: ...P MP ACN RIGID pavement 4 6 8 10 12 14 16 24000 28000 32000 36000 40000 44000 48000 52000 WEIGHT lb AIRCRAFT CLASSIFICATION NUMBER ACN 145AOM004 JUN 23 1999 D K 20 MN m3 C K 40 MN m3 B K 80 MN m3 A K...

Page 693: ...CLASSIFICATION NUMBER ACN 145AOM004 JUN 23 1999 D K 20 MN m3 C K 40 MN m3 B K 80 MN m3 A K 150 MN m3 EMB 145LR LU ACN RIGID PAVEMENT 4 6 8 10 12 14 16 26000 30000 34000 38000 42000 46000 50000 54000 W...

Page 694: ...tion detected during the calculation process These data are valid for the wind and temperature associated The data are calculated for four reference winds for range of temperatures The level off outpu...

Page 695: ...42512 124 124 135 R 43434 126 126 136 R 44346 127 127 138 R 4 90 4 39474 117 118 130 R 42391 124 124 135 R 43307 125 125 136 R 44234 127 127 137 R 6 90 7 39349 117 118 130 R 42269 123 123 134 R 43179...

Page 696: ...R 42201 R 43100 R 24 93 6 37783 R 40595 R 41496 R 42391 R Limitation codes 1 2 Obstacle No L Level off R Runway S Structural B Brake Energy W WAT V1 VR V2 Kt vs Weight and Temperature Temp Weight 4850...

Page 697: ...CH APPROACH CLIMB SPEED FLAPS 9 WEIGHT lb APPROACH CLIMB SPEED KIAS 27000 125 28000 128 29000 130 30000 132 31000 134 32000 136 33000 138 34000 140 35000 142 36000 144 37000 146 38000 148 39000 150 40...

Page 698: ...b FLAPS 45 FLAPS 22 27000 104 109 28000 106 111 29000 108 113 30000 109 114 31000 111 116 32000 113 118 33000 115 120 34000 117 121 35000 118 123 36000 120 125 37000 121 127 38000 123 128 39000 124 13...

Page 699: ...APPROACH SPEED VAPP VREF wind correction Wind correction steady headwind component gust increment above steady wind For Flaps 45 landing the minimum wind correction is 5 KIAS and the maximum is 15 KIA...

Page 700: ...PERFORMANCE EMB 145 A1 FAA AIRPLANE OPERATIONS MANUAL 1 04 25 Page 4 Code 02 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 701: ...the brakes and spoilers as deceleration device i e no engine reverse thrust is used The required landing distance for dispatch is the unfactored landing distance increased by the 66 7 for dry runway...

Page 702: ...0 Kt 20 Kt 10 Kt 0 Kt 10 Kt 20 Kt 43000 4406 3818 3632 3452 4513 3914 3725 3542 41000 4235 3664 3483 3308 4336 3755 3571 3393 39000 4066 3511 3336 3165 4161 3597 3419 3245 37000 3904 3364 3194 3027 39...

Page 703: ...10 27000 3393 2899 2742 2589 3468 2967 2809 2654 ALTITUDE Weight 8000 ft 9000 ft lb WIND kt 10 Kt 0 Kt 10 Kt 20 Kt 10 Kt 0 Kt 10 Kt 20 Kt 43000 5117 4463 4257 4057 5253 4588 4378 4175 41000 4905 4272...

Page 704: ...t 20 Kt 10 Kt 0 Kt 10 Kt 20 Kt 43000 3391 2912 2762 2616 3469 2983 2830 2682 41000 3277 2809 2661 2519 3351 2876 2726 2581 39000 3165 2707 2565 2429 3235 2770 2625 2484 37000 3054 2610 2473 2341 3121...

Page 705: ...92 27000 2684 2278 2149 2024 2740 2330 2199 2073 ALTITUDE Weight 8000 ft 9000 ft lb WIND kt 10 Kt 0 Kt 10 Kt 20 Kt 10 Kt 0 Kt 10 Kt 20 Kt 43000 3905 3379 3214 3053 4002 3468 3300 3137 41000 3768 3253...

Page 706: ...h Runways contaminated with compacted snow ice and wet ice are considered slippery once there is no impingent drag and the braking friction coefficient reduces Other contaminants such as standing wate...

Page 707: ...om the table x Current overspeed in kt 5 kt The unfactored landing distance on contaminated runways CULD becomes Additional Distance CULDREF x Final Altitude Correction Final Tailwind Correction Final...

Page 708: ...DRY SNOW 0 625 in WEIGHT lb FLAP 22 FLAP 45 29000 6033 4822 30000 6194 4946 31000 6357 5071 32000 6532 5201 33000 6707 5330 34000 6883 5459 35000 7058 5589 36000 7245 5721 37000 7436 5852 38000 7627 5...

Page 709: ...DRY SNOW 1 25 in WEIGHT lb FLAP 22 FLAP 45 29000 5276 4357 30000 5411 4464 31000 5546 4571 32000 5693 4683 33000 5839 4794 34000 5986 4905 35000 6132 5016 36000 6289 5129 37000 6448 5243 38000 6608 53...

Page 710: ...DRY SNOW 2 50 in WEIGHT lb FLAP 22 FLAP 45 29000 4411 3856 30000 4515 3943 31000 4619 4031 32000 4732 4122 33000 4845 4213 34000 4957 4304 35000 5070 4395 36000 5190 4488 37000 5313 4581 38000 5436 46...

Page 711: ...LAP 22 FLAP 45 29000 3944 3645 30000 4036 3734 31000 4129 3823 32000 4222 3909 33000 4315 3996 34000 4408 4082 35000 4501 4169 36000 4593 4250 37000 4685 4329 38000 4777 4409 39000 4868 4488 40000 496...

Page 712: ...11551 9411 30000 11556 9406 31000 11572 9412 32000 11656 9487 33000 11740 9561 34000 11824 9635 35000 11909 9709 36000 12032 9810 37000 12170 9921 38000 12308 10032 39000 12446 10143 40000 12584 10254...

Page 713: ...USH 0 15 in WET SNOW 0 25 in DRY SNOW 0 625 in WEIGHT ft FLAP 22 FLAP 45 29000 6323 4930 30000 6501 5059 31000 6682 5190 32000 6874 5330 33000 7065 5469 34000 7257 5609 35000 7449 5748 36000 7658 5890...

Page 714: ...USH 0 29 in WET SNOW 0 50 in DRY SNOW 1 25 in WEIGHT ft FLAP 22 FLAP 45 29000 5630 4558 30000 5783 4672 31000 5938 4788 32000 6103 4912 33000 6268 5035 34000 6433 5159 35000 6598 5282 36000 6777 5408...

Page 715: ...USH 0 59 in WET SNOW 1 00 in DRY SNOW 2 50 in WEIGHT ft FLAP 22 FLAP 45 29000 4885 4062 30000 5010 4160 31000 5137 4258 32000 5272 4363 33000 5407 4468 34000 5543 4573 35000 5678 4678 36000 5824 4784...

Page 716: ...ES COMPACTED SNOW WEIGHT ft FLAP 22 FLAP 45 29000 4001 3650 30000 4095 3739 31000 4189 3828 32000 4284 3915 33000 4378 4002 34000 4473 4089 35000 4567 4176 36000 4662 4259 37000 4756 4340 38000 4850 4...

Page 717: ...WEIGHT ft FLAP 22 FLAP 45 29000 11684 9401 30000 11691 9415 31000 11707 9436 32000 11775 9504 33000 11844 9572 34000 11913 9640 35000 11982 9708 36000 12110 9810 37000 12260 9924 38000 12410 10039 39...

Page 718: ...5 1 53 Inadvertent Spoiler Opening in Flight spoilers closed or floating Flaps 22 VREF 45 10 kt 1 35 Inadvertent Spoiler Opening in Flight spoilers open Flaps 22 VREF 45 10 kt 1 27 Inadvertent Stall P...

Page 719: ...Table must be used only when the brake temperature indication is not working properly according to the MMEL In this case if the landing weight exceeds the Quick Turn Around Weight a subsequent takeoff...

Page 720: ...4180 34640 40 29189 29598 30076 30556 30965 32438 32912 33424 33952 34409 44 29009 29414 29890 30368 30774 32224 32695 33204 33729 34183 48 28831 29232 29707 30182 30585 32013 32479 32987 33509 33959...

Page 721: ...558 34009 40 28688 29086 29560 30032 30433 31844 32307 32813 33332 33780 44 28510 28905 29376 29846 30244 31633 32092 32595 33111 33556 48 28335 28727 29196 29663 30059 31427 31881 32382 32895 33337 W...

Page 722: ...166 33611 36 28371 28764 29233 29701 30098 31470 31925 32427 32940 33383 40 28193 28581 29049 29515 29908 31258 31709 32209 32719 33158 44 28018 28403 28869 29332 29723 31051 31498 31995 32503 32939 W...

Page 723: ...545 32982 36 27874 28257 28721 29182 29571 30881 31324 31820 32325 32759 40 27699 28078 28541 28999 29385 30674 31113 31606 32108 32539 44 27528 27903 28364 28819 29203 30471 30906 31397 31896 32324 W...

Page 724: ...154 32585 32 27557 27933 28394 28850 29235 30506 30941 31433 31933 32361 36 27382 27755 28214 28667 29049 30299 30730 31220 31716 32141 40 27211 27580 28038 28489 28868 30096 30524 31011 31505 31927 W...

Page 725: ...540 31962 32 27065 27431 27887 28336 28713 29923 30347 30833 31324 31743 36 26894 27256 27710 28156 28531 29720 30140 30624 31112 31528 40 26725 27084 27537 27980 28352 29521 29936 30418 30903 31317 W...

Page 726: ...153 31569 28 26752 27113 27565 28009 28382 29552 29968 30450 30936 31349 32 26578 26936 27386 27828 28198 29347 29758 30239 30721 31132 36 26408 26762 27211 27650 28018 29146 29553 30031 30511 30919 W...

Page 727: ...547 30955 28 26260 26611 27058 27495 27860 28971 29375 29851 30328 30733 32 26088 26436 26881 27315 27678 28767 29167 29641 30116 30517 36 25920 26264 26708 27139 27500 28568 28965 29436 29908 30307 W...

Page 728: ...29207 29681 30156 30558 24 25945 26290 26734 27166 27527 28598 28995 29467 29939 30338 28 25774 26115 26557 26986 27345 28395 28788 29258 29727 30123 32 28196 28585 29053 29519 29912 WIND Temp 10 kt...

Page 729: ...103 27464 28528 28923 29394 29865 30264 24 25721 26061 26503 26931 27289 28333 28725 29194 29662 30057 28 28146 28534 29001 29466 29859 32 27963 28348 28812 29275 29665 WIND Temp 10 kt 20 kt O C SLOPE...

Page 730: ...6493 36943 40 31395 31788 32198 32589 32986 34906 35346 35817 36251 36697 44 31207 31597 31999 32388 32783 34675 35112 35581 36012 36455 48 31022 31410 31805 32191 32583 34448 34882 35348 35777 36217...

Page 731: ...827 36267 40 30836 31221 31608 31992 32381 34264 34696 35161 35587 36025 44 30593 30974 31351 31732 32117 34037 34466 34929 35353 35787 48 30354 30732 31099 31477 31859 33815 34241 34702 35123 35554 W...

Page 732: ...406 35841 36 30400 30778 31147 31526 31909 33858 34284 34745 35167 35599 40 30157 30531 30890 31266 31645 33631 34054 34513 34932 35361 44 29918 30289 30638 31010 31386 33408 33829 34286 34702 35127 W...

Page 733: ...745 35171 36 29722 30090 30431 30801 31174 33226 33644 34099 34513 34936 40 29490 29854 30186 30553 30923 33010 33425 33878 34289 34709 44 29262 29623 29945 30310 30676 32798 33210 33661 34070 34487 W...

Page 734: ...334 34755 32 29299 29661 29985 30349 30717 32832 33245 33697 34106 34523 36 29067 29426 29740 30101 30465 32616 33026 33476 33882 34297 40 28841 29196 29500 29859 30220 32405 32813 33260 33664 34075 W...

Page 735: ...699 34112 32 28652 29004 29300 29657 30015 32224 32629 33074 33475 33884 36 28460 28810 29098 29452 29808 32018 32420 32856 33255 33662 40 28273 28619 28900 29252 29605 31817 32216 32643 33040 33443 W...

Page 736: ...457 32851 33252 36 31439 31833 32244 32636 33033 WIND Temp 10 kt 20 kt O C SLOPE 2 1 0 1 2 2 1 0 1 2 20 36055 36511 36993 37441 37904 37396 37869 38364 38828 39310 15 35680 36131 36610 37053 37510 370...

Page 737: ...31638 32023 32412 WIND Temp 10 kt 20 kt O C SLOPE 2 1 0 1 2 2 1 0 1 2 20 35342 35788 36264 36703 37155 36644 37108 37596 38052 38523 15 34975 35415 35888 36322 36769 36257 36715 37200 37650 38116 10...

Page 738: ...007 WIND Temp 10 kt 20 kt O C SLOPE 2 1 0 1 2 2 1 0 1 2 20 34639 35074 35544 35974 36416 35903 36356 36837 37284 37744 15 34282 34713 35179 35605 36042 35527 35975 36453 36895 37349 10 33942 34368 348...

Page 739: ...703 WIND Temp 10 kt 20 kt O C SLOPE 2 1 0 1 2 2 1 0 1 2 20 34299 34730 35196 35623 36060 35545 35994 36471 36913 37368 15 33950 34376 34839 35261 35693 35177 35620 36094 36532 36981 10 33612 34034 344...

Page 740: ...3389 43978 40 37492 38028 38626 39247 39786 41186 41771 42412 43088 43673 44 37248 37782 38376 38994 39530 40903 41484 42121 42793 43374 48 37010 37540 38132 38746 39280 40625 41203 41837 42504 43082...

Page 741: ...565 43144 40 36817 37345 37935 38546 39077 40401 40975 41607 42271 42846 44 36579 37104 37691 38298 38827 40123 40694 41322 41982 42554 48 36346 36868 37452 38056 38581 39852 40419 41044 41700 42268 W...

Page 742: ...048 42621 36 36391 36914 37498 38103 38629 39904 40472 41098 41754 42324 40 36154 36673 37255 37856 38379 39627 40191 40814 41466 42032 44 35922 36438 37017 37614 38135 39357 39917 40537 41185 41748 W...

Page 743: ...238 41801 36 35729 36243 36820 37414 37932 39132 39690 40307 40952 41512 40 35498 36009 36583 37174 37689 38863 39418 40031 40672 41229 44 35273 35781 36353 36940 37453 38601 39152 39763 40400 40953 W...

Page 744: ...729 41286 32 35310 35818 36390 36979 37491 38644 39195 39806 40444 40998 36 35077 35583 36152 36737 37247 38373 38921 39529 40162 40713 40 34847 35349 35916 36497 37004 38104 38649 39254 39883 40431 W...

Page 745: ...929 40477 32 34649 35149 35713 36292 36796 37873 38415 39017 39644 40188 36 34419 34916 35478 36052 36554 37605 38144 38743 39365 39906 40 34193 34687 35246 35818 36317 37342 37877 38473 39091 39629 W...

Page 746: ...416 39958 32 34226 34720 35280 35852 36351 37381 37916 38512 39131 39669 36 33992 34483 35040 35609 36105 37108 37640 38233 38848 39383 40 33763 34252 34806 35371 35864 36841 37369 37959 38570 39102 W...

Page 747: ...616 39148 32 33567 34053 34605 35167 35658 36613 37138 37725 38333 38862 36 33339 33822 34371 34930 35418 36347 36868 37453 38056 38582 40 33116 33596 34142 34698 35183 36087 36605 37186 37786 38308 W...

Page 748: ...107 38633 24 33148 33628 34175 34731 35217 36124 36643 37225 37825 38348 28 32920 33397 33942 34494 34978 35858 36374 36952 37549 38068 32 32697 33172 33713 34263 34743 35599 36111 36687 37279 37795 W...

Page 749: ...323 37840 24 32506 32978 33517 34063 34542 35375 35885 36458 37047 37560 28 32283 32752 33289 33832 34308 35116 35622 36192 36777 37287 32 32065 32532 33066 33606 34078 34862 35365 35932 36513 37021 W...

Page 750: ...826 37337 20 32096 32562 33097 33637 34110 34898 35401 35968 36550 37058 24 31874 32338 32870 33407 33877 34639 35139 35703 36281 36786 28 31657 32118 32647 33181 33649 34386 34883 35444 36018 36520 W...

Page 751: ...6068 46585 40 39911 40440 40932 41534 42029 43987 44560 45099 45757 46273 44 39658 40185 40674 41272 41766 43693 44263 44799 45452 45966 48 39411 39935 40421 41016 41508 43404 43972 44504 45154 45666...

Page 752: ...213 45726 40 39207 39730 40213 40805 41297 43167 43732 44261 44908 45419 44 38960 39479 39960 40549 41039 42879 43440 43967 44609 45119 48 38718 39235 39713 40298 40787 42597 43156 43678 44317 44826 W...

Page 753: ...674 45184 36 38761 39279 39757 40343 40832 42648 43207 43730 44370 44878 40 38514 39029 39504 40087 40575 42359 42915 43436 44071 44578 44 38271 38783 39256 39835 40322 42076 42629 43146 43777 44283 W...

Page 754: ...830 44336 36 38067 38577 39047 39624 40110 41839 42389 42903 43531 44036 40 37824 38332 38799 39372 39857 41555 42103 42614 43238 43741 44 37586 38091 38556 39126 39609 41278 41822 42330 42951 43452 W...

Page 755: ...295 43798 32 37624 38129 38594 39164 39648 41322 41866 42375 42996 43498 36 37381 37884 38346 38913 39395 41039 41581 42085 42703 43203 40 37143 37643 38102 38666 39147 40761 41300 41802 42415 42914 W...

Page 756: ...461 42961 32 36938 37436 37893 38454 38934 40523 41059 41558 42168 42666 36 36700 37196 37650 38208 38687 40246 40779 41275 41881 42378 40 36468 36961 37413 37967 38445 39975 40506 40998 41601 42096 W...

Page 757: ...932 42429 28 36501 36994 37446 38001 38479 40013 40544 41037 41640 42135 32 36263 36753 37203 37754 38231 39735 40263 40753 41352 41846 36 36030 36518 36965 37513 37989 39464 39989 40476 41071 41564 W...

Page 758: ...116 41609 28 35829 36315 36759 37305 37779 39230 39752 40236 40829 41320 32 35595 36079 36520 37063 37536 38958 39477 39958 40547 41037 36 35367 35848 36287 36826 37298 38691 39208 39686 40271 40759 W...

Page 759: ...597 41087 24 35399 35880 36319 36859 37331 38728 39246 39723 40309 40798 28 35165 35644 36080 36617 37088 38456 38970 39445 40027 40515 32 34937 35413 35847 36380 36851 38190 38702 39173 39751 40238 W...

Page 760: ...794 40281 24 34739 35213 35645 36176 36645 37960 38469 38938 39513 39998 28 34511 34983 35412 35940 36408 37694 38200 38666 39237 39721 32 34287 34757 35183 35707 36174 37433 37936 38399 38967 39450 W...

Page 761: ...285 39770 20 34316 34786 35213 35738 36205 37467 37971 38434 39002 39485 24 34088 34556 34980 35501 35967 37201 37702 38162 38727 39208 28 33864 34329 34750 35269 35734 36940 37438 37895 38456 38936 W...

Page 762: ...PERFORMANCE EMB 145 135 FAA AIRPLANE OPERATIONS MANUAL 1 04 30 Page 62 Code 02 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 763: ...runway analysis software for determination of the limiting weights THE LANDING OUTPUT DATA The program outputs the limit weight the code for the limitation detected the approach climb speed the refere...

Page 764: ...3243 42549 S 156 129 37061 42549 S 156 129 38409 42549 S 156 129 39854 10 42549 S 156 129 32952 42549 S 156 129 36715 42549 S 156 129 38044 42549 S 156 129 39469 15 42549 S 156 129 32672 42549 S 156 1...

Page 765: ...Planning 1 05 05 APU and Engine Fuel Consumption 1 05 07 Climb 1 05 10 Cruise 1 05 15 Descent 1 05 20 Holding 1 05 25 One Engine Inoperative Performance 1 05 30 Flight with Landing Gear Down 1 05 35...

Page 766: ...mplified flight planning and one engine inoperative are included NOTE Airplanes equipped with Rolls Royce AE3007A1P engines should use the same simplified flight planning climb cruise descent holding...

Page 767: ...move as far as the line indicating cruise pressure altitude and read the trip fuel To determine trip time enter trip ground distance correct for wind condition move as far as the referring cruise pres...

Page 768: ...p fuel The allowances below may be used PHASE OF FLIGHT FUEL CONSUMPTION lb min TAXI 15 40 APU 2 73 EXAMPLE Given DESTINATION AIRPORT Trip Distance 400 NM Flight Level FL 350 Cruise Speed LRC Wind 30...

Page 769: ...e 1600 lb Reserve Fuel 145 lb 5 of Trip Fuel From Holding Tables Fuel consumption at 1500 ft 1563 lb h For 30 min of holding fuel 782 lb To determine the TOTAL FUEL ON TAKEOFF let s consider 5 minutes...

Page 770: ...2500 2000 1500 1000 500 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 8500 9000 9500 0 200 400 600 800 1000 1200 1400 1600 145AOMFAA001 09OCT2002 TRIP DISTANCE NM LA...

Page 771: ...3500 3000 2500 2000 1500 1000 500 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 8500 9000 9500 0 200 400 600 800 1000 1200 1400 1600 LANDING WEIGHT lb TAIL HEAD 145A...

Page 772: ...15 10 5 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 105 110 115 120 125 130 135 140 145 150 155 160 165 170 175 180 185 190 195 200 205 210 215 220 225 230 235 240 245 250 255 260 0...

Page 773: ...5 40 35 30 25 20 15 10 5 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 105 110 115 120 125 130 135 140 145 150 155 160 165 170 175 180 185 190 195 200 205 210 215 220 225 230 235 240 2...

Page 774: ...ferent flight levels are calculated A or B based on the following assumptions Condition A The flight level was calculated based only on minimum fuel consumption It may result on reduced time in levele...

Page 775: ...180 230 320 370 370 370 370 40000 B 60 110 130 160 210 250 300 370 A 70 170 240 330 370 370 370 370 38000 B 80 100 120 170 220 260 330 370 A 140 190 250 340 370 370 370 370 36000 B 80 100 120 170 220...

Page 776: ...7A1P ENGINES MAX SPEED CRUISE CRUISE THRUST LIMITED ISA C Weight lb 10 5 0 5 10 15 20 25 30 35 50000 370 370 370 370 370 360 340 320 390 280 48000 370 370 370 370 370 370 360 340 310 290 46000 370 370...

Page 777: ...be used in flight where the wind information is available and more accurate Evaluation Method 1 Check the wind factors for actual and new altitudes 2 Calculate the difference between new and actual wi...

Page 778: ...27 26000 0 6 11 16 22 27 33 38 44 50 56 28000 0 6 12 18 23 28 33 39 45 50 56 30000 0 6 12 18 24 29 34 40 45 50 56 32000 0 6 12 18 24 30 35 40 45 51 56 34000 0 6 12 18 24 30 36 41 46 51 57 36000 0 6 1...

Page 779: ...145 168 191 28000 0 18 37 54 71 89 108 127 148 170 193 30000 0 17 36 55 76 92 111 130 150 172 194 32000 0 17 34 53 73 95 113 132 152 173 195 34000 0 16 33 51 70 91 113 133 153 173 194 36000 0 15 31 49...

Page 780: ...FLIGHT PLANNING EMB 145 A1 and A1P LB AIRPLANE OPERATIONS MANUAL 1 05 05 Page 14 Code 02 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 781: ...even fuel price is the price at departure multiplied by the fuel surplus ratio If break even fuel price is lower than destination price it is economically feasible to execute fuel tankering The additi...

Page 782: ...33000 FT AND ABOVE 200 1 02 1 02 400 1 04 1 04 600 1 06 1 06 800 1 08 1 08 1000 1 10 1 10 1200 1 12 1 12 1400 1 14 1 13 1600 1 16 1 16 1800 1 19 1 18 2000 1 20 FUEL TANKERING MAXIMUM SPEED CRUISE AE3...

Page 783: ...AIR BLEED APU GEN LOAD APU FUEL FLOW lb min No Load No Load 1 59 0 0 Max Load 1 70 2 Packs No Load 2 49 Max Load 2 73 No Load No Load 1 82 140 Max Load 1 94 2 Packs No Load 2 59 5000 Max Load 2 85 No...

Page 784: ...established for taxi take off approach and go around fuel consumption should be considered when calculating detailed flight plans FUEL CONSUMPTION ENGINE PHASE OF FLIGHT FUEL CONSUMPTION lb min TAXI...

Page 785: ...ended when maximum rate of climb is desired in order to reach an altitude on minimum climb time The recommended maximum rate of climb speed is related to flaps up all engines operating and is function...

Page 786: ...a are shown for various takeoff weights ISA deviations and cruise altitudes The takeoff fuel consumption is not considered in the following tables Tables presents the scheduled climb speed according t...

Page 787: ...eparture airport obtained from interpolation from the Sea Level to 5000 ft climb table Fuel 93 6 lb Distance 4 3 NM Time 1 4 min Data provided from the Sea Level to 33000 ft Top of Climb table Fuel 96...

Page 788: ...FLIGHT PLANNING EMB 145 A1 and A1P LB AIRPLANE OPERATIONS MANUAL 1 05 10 Page 4 Code 02 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 789: ...6 212 44000 DISTANCE NM 7 7 7 8 10 8 9 9 9 12 TIME MIN 2 2 2 2 2 2 2 2 2 3 FUEL LB 129 134 139 145 164 155 161 167 174 198 42000 DISTANCE NM 6 7 7 7 9 8 8 8 9 11 TIME MIN 2 2 2 2 2 2 2 2 2 3 FUEL LB 1...

Page 790: ...NCE NM 10 10 11 11 14 12 12 13 13 17 TIME MIN 2 3 3 3 3 3 3 3 3 4 FUEL LB 181 188 195 204 232 207 215 224 234 267 42000 DISTANCE NM 9 10 10 11 14 11 11 12 12 16 TIME MIN 2 2 2 2 3 3 3 3 3 4 FUEL LB 17...

Page 791: ...15 20 15 16 16 17 22 TIME MIN 3 3 3 4 4 4 4 4 4 5 FUEL LB 234 243 253 264 302 261 271 282 294 338 42000 DISTANCE NM 12 13 13 14 18 14 15 15 16 21 TIME MIN 3 3 3 3 4 3 3 4 4 5 FUEL LB 219 227 237 247 2...

Page 792: ...5 5 5 6 FUEL LB 288 300 312 326 376 318 331 344 360 419 42000 DISTANCE NM 16 17 17 18 24 18 19 20 21 27 TIME MIN 4 4 4 4 5 4 4 4 5 6 FUEL LB 270 280 292 305 350 298 309 322 336 389 40000 DISTANCE NM...

Page 793: ...6 6 6 8 FUEL LB 350 364 379 396 466 383 398 414 434 516 42000 DISTANCE NM 21 21 22 24 32 23 24 25 27 36 TIME MIN 5 5 5 5 7 5 5 5 6 8 FUEL LB 327 340 354 370 433 358 372 387 405 479 40000 DISTANCE NM...

Page 794: ...7 7 7 7 10 FUEL LB 417 433 451 473 569 451 470 489 513 624 42000 DISTANCE NM 26 27 28 30 41 29 30 32 34 47 TIME MIN 6 6 6 6 8 6 6 7 7 9 FUEL LB 389 404 421 441 527 421 438 456 478 577 40000 DISTANCE...

Page 795: ...1 8 8 8 9 12 FUEL LB 487 507 528 555 683 519 540 563 593 736 42000 DISTANCE NM 32 34 35 37 53 35 37 38 41 58 TIME MIN 7 7 7 8 10 7 8 8 8 11 FUEL LB 453 472 491 516 630 483 503 524 551 678 40000 DISTAN...

Page 796: ...9 9 9 13 9 9 9 10 14 FUEL LB 548 570 594 627 782 575 599 624 659 825 42000 DISTANCE NM 38 39 41 44 63 40 42 44 47 68 TIME MIN 8 8 8 9 12 8 9 9 9 13 FUEL LB 509 530 552 582 719 535 557 580 612 758 400...

Page 797: ...10 10 15 10 10 10 11 16 FUEL LB 602 627 653 691 867 629 655 682 723 909 42000 DISTANCE NM 43 45 46 50 72 45 47 49 53 77 TIME MIN 9 9 9 10 14 9 9 10 10 14 FUEL LB 559 583 607 641 796 584 608 634 670 8...

Page 798: ...1 12 17 11 11 12 12 18 FUEL LB 655 683 711 754 952 682 711 741 786 995 42000 DISTANCE NM 48 50 52 56 82 50 52 55 59 87 TIME MIN 10 10 10 11 15 10 10 11 11 16 FUEL LB 608 634 660 699 873 633 660 687 72...

Page 799: ...13 19 12 12 13 14 20 FUEL LB 709 739 770 818 1038 737 768 800 851 1081 42000 DISTANCE NM 53 55 58 63 92 56 58 61 66 97 TIME MIN 11 11 11 12 17 11 11 12 12 18 FUEL LB 658 685 714 758 950 683 712 742 78...

Page 800: ...21 13 14 14 15 21 FUEL LB 765 797 831 883 1123 794 828 863 916 1164 42000 DISTANCE NM 59 61 64 69 102 62 65 68 73 107 TIME MIN 12 12 12 13 19 12 13 13 14 20 FUEL LB 708 739 770 817 1025 735 766 798 84...

Page 801: ...16 24 FUEL LB 840 871 908 965 1206 870 916 953 1016 1248 42000 DISTANCE NM 67 68 71 77 112 70 72 75 81 118 TIME MIN 13 13 14 14 20 14 14 14 15 21 FUEL LB 777 806 839 891 1100 804 846 880 937 1138 400...

Page 802: ...17 18 26 FUEL LB 900 947 985 1051 1293 931 977 1017 1086 1339 42000 DISTANCE NM 74 75 79 85 123 77 79 82 89 130 TIME MIN 14 15 15 16 22 15 15 16 17 23 FUEL LB 831 873 909 968 1177 858 901 938 999 121...

Page 803: ...20 29 FUEL LB 961 1009 1050 1122 1388 1036 1062 1058 1127 1457 42000 DISTANCE NM 81 83 86 94 136 87 89 90 98 144 TIME MIN 16 16 16 17 25 17 17 17 18 26 FUEL LB 886 929 967 1032 1259 953 977 973 1035 1...

Page 804: ...098 1094 1167 1530 1108 1136 1133 1209 1586 42000 DISTANCE NM 91 93 95 103 151 96 98 100 109 159 TIME MIN 18 18 18 19 27 19 19 19 20 29 FUEL LB 983 1008 1005 1070 1380 1016 1041 1039 1107 1426 40000 D...

Page 805: ...TIME MIN 22 22 22 24 35 FUEL LB 1151 1180 1178 1256 1650 42000 DISTANCE NM 102 104 106 115 169 TIME MIN 20 20 20 21 31 FUEL LB 1052 1078 1077 1146 1478 40000 DISTANCE NM 93 94 96 104 150 TIME MIN 18 1...

Page 806: ...FLIGHT PLANNING EMB 145 A1 and A1P LB AIRPLANE OPERATIONS MANUAL 1 05 10 Page 22 Code 02 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 807: ...CRUISE MANEUVER CAPABILITY NOTE The recommended cruise altitude must ensure a maneuver load factor of 1 3 g before buffet onset LOAD FACTOR 45450 lb 42000 lb 38000 lb 34000 lb 30000 lb 26500 lb 20000...

Page 808: ...FLIGHT PLANNING EMB 145 A1 and A1P LB AIRPLANE OPERATIONS MANUAL 1 05 15 Page 2 Code 02 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 809: ...fic range It is used when range is the principal factor In the maximum speed schedule the airplane is flown in a speed resulting from maximum cruise power setting It is used when minimum flight time i...

Page 810: ...15 0 523 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 SR NM LB 0 107 0 117 0 119 0 121 0 123 0 126 0 128 0 130 0 132 0 134 N1 65 3 69 7 70 1 70 6 71 1 71 7 72 3 72 9 73 6 74 3 F F...

Page 811: ...5 0 482 0 489 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 SR NM LB 0 114 0 127 0 13 0 133 0 136 0 138 0 141 0 144 0 147 0 149 N1 62 5 65 6 66 2 66 8 67 4 68 68 5 69 69 5 70 F FLO...

Page 812: ...1 898 884 872 860 849 839 828 819 809 IAS KT 228 221 220 219 217 216 215 214 213 212 31000 TAS KT 243 255 257 259 262 264 267 270 273 276 INDICATED MACH 0 377 0 401 0 406 0 411 0 417 0 423 0 429 0 435...

Page 813: ...14 0 627 BUFFET MARGIN G 2 51 2 47 2 43 2 38 2 33 2 28 2 24 2 19 2 14 2 09 SR NM LB 0 136 0 138 0 140 0 142 0 144 0 147 0 149 0 152 0 154 0 157 N1 75 75 8 76 7 77 6 78 4 79 2 80 80 6 81 2 81 9 F FLOW...

Page 814: ...0 565 0 577 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 53 2 49 2 44 2 38 2 33 2 29 SR NM LB 0 152 0 155 0 157 0 16 0 163 0 165 0 168 0 17 0 173 0 176 N1 70 6 71 2 71 9 72 6 73 3 74 1 75 75 9 76 8 77 6 F FL...

Page 815: ...801 793 786 780 773 768 763 758 752 748 IAS KT 211 210 209 208 207 206 205 204 203 202 31000 TAS KT 279 282 285 289 292 296 299 303 306 310 INDICATED MACH 0 454 0 461 0 469 0 476 0 484 0 492 0 500 0 5...

Page 816: ...738 0 757 0 767 BUFFET MARGIN G 2 04 1 98 1 91 1 84 1 77 1 68 1 59 1 49 1 41 SR NM LB 0 159 0 161 0 164 0 166 0 168 0 171 0 173 0 176 0 178 N1 82 7 83 4 84 2 84 8 85 4 86 2 87 1 88 5 90 1 F FLOW LB H...

Page 817: ...57 0 673 0 689 0 706 BUFFET MARGIN G 2 25 2 2 2 15 2 09 2 04 1 97 1 91 1 83 1 75 SR NM LB 0 179 0 182 0 185 0 188 0 191 0 194 0 197 0 199 0 202 N1 78 4 79 1 79 7 80 4 81 1 81 9 82 7 83 3 84 3 F FLOW L...

Page 818: ...H ENG 745 743 741 740 738 737 737 738 742 IAS KT 201 200 200 199 198 198 198 198 199 31000 TAS KT 314 318 322 327 331 337 343 349 357 INDICATED MACH 0 533 0 542 0 552 0 562 0 573 0 585 0 598 0 612 0...

Page 819: ...585 0 596 0 607 0 618 0 629 0 641 0 653 0 665 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 SR NM LB 0 107 0 105 0 106 0 108 0 109 0 111 0 112 0 114 0 115 0 116 N1 65 7 77 4 78 2 7...

Page 820: ...0 598 0 608 0 62 0 631 0 643 0 655 0 667 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 SR NM LB 0 114 0 110 0 111 0 113 0 115 0 116 0 118 0 12 0 121 0 123 N1 63 6 76 0 76 7 77 4 78...

Page 821: ...79 2 80 0 80 8 F FLOW LB H ENG 1093 1578 1574 1571 1568 1566 1564 1563 1563 1563 IAS KT 250 320 320 320 320 320 320 320 320 320 31000 TAS KT 267 365 370 375 381 386 392 398 404 410 INDICATED MACH 0 4...

Page 822: ...703 0 715 0 719 0 728 0 738 0 747 0 751 0 750 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 53 2 40 2 29 2 19 SR NM LB 0 118 0 119 0 120 0 122 0 124 0 127 0 130 0 133 0 137 0 141 N1 84 5 85 2 85 9 8...

Page 823: ...0 719 0 733 0 747 0 761 0 769 0 770 0 772 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 55 SR NM LB 0 124 0 126 0 127 0 129 0 13 0 132 0 133 0 135 0 14 0 144 N1 83 1 83 7 84 3 85 85 7...

Page 824: ...86 5 86 4 F FLOW LB ENG 1564 1565 1567 1570 1573 1577 1581 1585 1544 1488 IAS KT 320 320 320 320 320 320 320 320 315 309 31000 TAS KT 416 422 428 435 441 448 455 462 462 460 INDICATED MACH 0 68 0 692...

Page 825: ...753 0 752 0 757 0 762 0 771 0 779 0 780 0 780 0 767 BUFFET MARGIN G 2 08 1 99 1 89 1 79 1 69 1 59 1 52 1 44 1 41 SR NM LB 0 146 0 150 0 154 0 158 0 162 0 166 0 170 0 174 0 178 N1 87 9 87 9 88 88 5 88...

Page 826: ...CH 0 775 0 777 0 78 0 78 0 78 0 78 0 78 0 78 0 78 BUFFET MARGIN G 2 43 2 31 2 19 2 1 2 1 91 1 82 1 73 1 65 SR NM LB 0 149 0 154 0 16 0 165 0 171 0 177 0 183 0 188 0 194 N1 87 7 87 5 87 4 87 2 87 1 87...

Page 827: ...86 1 85 8 85 7 85 5 85 8 F FLOW LB H ENG 1435 1384 1335 1289 1240 1188 1138 1092 1052 IAS KT 302 296 289 283 277 271 264 258 252 31000 TAS KT 458 457 455 453 451 449 447 445 445 INDICATED MACH 0 78 0...

Page 828: ...FLIGHT PLANNING EMB 145 A1 and A1P LB AIRPLANE OPERATIONS MANUAL 1 05 15 Page 22 Code 02 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 829: ...n distance and time from the top of descent to sea level for various cruise altitudes The data are calculated for flight idle thrust setting maintaining 250 KIAS up to 10000 ft and 240 KIAS below 1000...

Page 830: ...5000 ft Top of Descent to Sea Level table Fuel 227 lb Distance 87 NM Time 16 min Data for 5000 ft 3500 ft 1500 ft above arrival airport obtained from the 5000 ft descent table Fuel 53 lb Distance 12 N...

Page 831: ...5 17 18 FUEL LB 55 99 137 171 198 220 242 250 44000 DIST NM 13 26 38 52 65 78 92 98 TIME MIN 3 6 9 11 13 15 17 18 FUEL LB 55 98 135 168 194 216 237 246 42000 DIST NM 13 25 38 51 64 77 90 96 TIME MIN 3...

Page 832: ...FLIGHT PLANNING EMB 145 A1 and A1P LB AIRPLANE OPERATIONS MANUAL 1 05 20 Page 4 Code 02 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 833: ...how indicated airspeed Mach number N1 fuel flow and fuel consumption for various weights altitudes anti ice on with and without ice accretion and off condition Data are presented in ISA condition for...

Page 834: ...7 9 46000 MACH 0 265 0 270 0 282 0 303 0 329 0 363 0 406 0 462 0 572 N1 55 6 56 6 59 3 63 5 67 7 71 4 76 2 80 3 87 4 FF LB H ENG 1018 1003 972 939 918 909 908 914 952 FC LB H 2036 2005 1943 1877 1836...

Page 835: ...6 267 6 34000 MACH 0 243 0 247 0 256 0 271 0 291 0 316 0 348 0 389 0 470 N1 48 5 49 3 51 6 55 4 59 6 64 0 67 9 72 5 79 0 FF LB H ENG 814 796 759 716 686 666 655 654 661 FC LB H 1629 1592 1517 1433 137...

Page 836: ...46000 MACH 0 302 0 311 0 331 0 363 0 399 0 440 0 487 0 541 0 630 N1 57 1 58 2 60 8 65 0 68 8 72 6 77 4 81 5 89 3 FF LB H ENG 1183 1165 1126 1081 1050 1034 1030 1033 1073 FC LB H 2367 2329 2252 2163 21...

Page 837: ...9 8 34000 MACH 0 302 0 311 0 331 0 363 0 399 0 440 0 487 0 541 0 630 N1 52 3 53 3 55 8 59 7 63 9 67 7 71 4 76 4 82 3 FF LB H ENG 1033 1014 972 922 883 855 841 842 851 FC LB H 2067 2027 1944 1844 1765...

Page 838: ...MACH 0 302 0 311 0 331 0 363 0 399 0 440 0 487 0 541 0 630 N1 57 1 58 2 60 8 65 0 68 8 72 6 77 4 81 5 89 3 FF LB H ENG 1316 1292 1241 1181 1135 1106 1092 1088 1123 FC LB H 2631 2584 2483 2362 2271 221...

Page 839: ...4000 MACH 0 302 0 311 0 331 0 363 0 399 0 440 0 487 0 541 0 630 N1 52 3 53 3 55 8 59 7 63 9 67 7 71 4 76 4 82 3 FF LB H ENG 1168 1143 1090 1024 970 928 902 893 893 FC LB H 2335 2286 2179 2047 1939 185...

Page 840: ...FLIGHT PLANNING EMB 145 A1 and A1P LB AIRPLANE OPERATIONS MANUAL 1 05 25 Page 8 Code 02 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 841: ...ng range cruise tables show N1 fuel flow indicated airspeed true airspeed indicated Mach number buffet margin and specific range Data are presented for various weights altitudes and corrections for IS...

Page 842: ...FLOW LB H ENG 2133 2120 2114 2111 2108 2111 2113 2114 IAS KT 239 237 236 235 234 233 232 232 44000 TAS KT 257 262 269 272 275 278 281 285 INDICATED MACH 0 394 0 406 0 419 0 425 0 431 0 438 0 445 0 452...

Page 843: ...392 0 398 0 404 0 411 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 SR NM LB 0 139 0 144 0 149 0 152 0 154 0 156 0 159 0 161 N1 72 5 73 6 74 9 75 6 76 5 77 2 78 1 78 9 F FLOW LB H ENG 1578 1...

Page 844: ...282 280 274 262 INDICATED MACH 0 460 0 467 0 456 0 456 0 453 0 446 0 428 BUFFET MARGIN G 2 55 2 52 2 32 2 22 2 11 1 97 1 74 SR NM LB 0 136 0 137 0 139 0 141 0 142 0 143 0 141 N1 87 0 87 7 88 4 88 6 8...

Page 845: ...0 444 0 452 0 461 0 467 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 52 SR NM LB 0 163 0 165 0 168 0 170 0 172 0 174 0 176 0 177 N1 79 7 80 5 81 3 81 9 82 7 83 4 84 3 85 2 F FLOW LB H ENG 1496...

Page 846: ...G IAS KT 46000 TAS KT INDICATED MACH BUFFET MARGIN G SR NM LB N1 F FLOW LB H ENG IAS KT 44000 TAS KT INDICATED MACH BUFFET MARGIN G SR NM LB N1 F FLOW LB H ENG IAS KT 42000 TAS KT INDICATED MACH BUFFE...

Page 847: ...85 9 86 6 87 5 88 7 90 2 91 1 90 9 91 9 F FLOW LB H ENG 1497 1500 1505 1513 1521 1511 1459 1431 IAS KT 199 198 197 197 196 194 186 180 32000 TAS KT 281 284 288 292 296 297 291 287 INDICATED MACH 0 465...

Page 848: ...profile The airplane should level off at the gross altitude and weight shown in the driftdown table NET LEVEL OFF ALTITUDE Federal regulations require terrain clearance flight planning based on net pe...

Page 849: ...BELOW ISA 15 ISA 20 17900 17700 17400 50000 48000 179 13800 13700 12900 19100 19000 18800 48000 46100 176 14400 14300 14000 20770 20640 20220 46000 44200 172 16010 15930 15690 22030 21880 21470 44000...

Page 850: ...800 11300 48000 45700 176 11500 11400 10900 8800 7500 17190 17090 15980 14260 12630 46000 43600 173 13220 13030 12280 10670 8550 18730 18540 17480 15620 13850 44000 42000 169 14620 14410 13460 11890 1...

Page 851: ...ber N1 fuel flow and fuel consumption for various weights and altitudes Data are presented in ISA condition for all engines operating and one engine inoperative configuration For both conditions table...

Page 852: ...IAS KT 173 168 164 161 161 TAS KT 172 3 179 6 189 1 201 3 217 1 44000 Mach 0 261 0 277 0 298 0 323 0 355 N1 71 3 75 1 79 7 84 3 89 FF LB H ENG 1730 1711 1717 1747 1804 FC LB H 1730 1711 1717 1747 180...

Page 853: ...266 0 284 0 308 0 338 0 377 N1 62 6 66 4 70 3 74 4 79 3 83 8 90 3 FF LB H ENG 1290 1242 1215 1208 1220 1252 1306 FC LB H 1290 1242 1215 1208 1220 1252 1306 IAS KT 156 149 143 139 135 133 133 TAS KT 1...

Page 854: ...2033 IAS KT 200 200 200 200 TAS KT 199 8 214 8 231 4 249 8 44000 Mach 0 302 0 331 0 363 0 399 N1 72 6 76 3 80 7 85 2 FF LB H ENG 1963 1935 1930 1954 FC LB H 1963 1935 1930 1954 IAS KT 200 200 200 200...

Page 855: ...TAS KT 198 7 213 6 230 1 248 4 268 8 32000 Mach 0 302 0 331 0 363 0 399 0 44 N1 67 2 70 9 74 6 79 2 83 4 FF LB H ENG 1637 1593 1567 1561 1580 FC LB H 1637 1593 1567 1561 1580 IAS KT 200 200 200 200 2...

Page 856: ...FLIGHT PLANNING EMB 145 A1 and A1P LB FAA AIRPLANE OPERATIONS MANUAL 1 05 30 Page 16 Code 03 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 857: ...this case the applicable AFM supplement must be observed for takeoff driftdown and landing performance penalties On board flight planning in case of landing gear not retracting after takeoff OPERATION...

Page 858: ...all procedures will be performed with the landing gear down and during the cruise phase the fuel quantity should be monitored throughout the flight CLIMB FLIGHT WITH LANDING GEAR DOWN The climb planni...

Page 859: ...239 249 261 307 278 288 300 314 371 46000 DISTANCE NM 7 7 8 8 11 9 9 10 10 13 TIME MIN 3 3 3 3 4 4 4 4 4 5 FUEL LB 195 203 211 220 254 235 244 253 265 307 42000 DISTANCE NM 6 6 7 7 9 7 8 8 9 11 TIME...

Page 860: ...368 437 374 388 403 423 504 46000 DISTANCE NM 11 11 11 12 16 12 13 13 14 19 TIME MIN 4 4 4 5 6 5 5 5 5 7 FUEL LB 275 285 296 310 360 315 327 340 355 414 42000 DISTANCE NM 9 9 10 10 13 10 11 11 12 16...

Page 861: ...72 472 490 510 535 643 46000 DISTANCE NM 14 15 15 16 22 16 17 18 19 25 TIME MIN 6 6 6 6 8 6 6 7 7 9 FUEL LB 355 369 384 401 469 396 412 428 448 525 42000 DISTANCE NM 12 12 13 14 18 14 14 15 16 21 TIME...

Page 862: ...74 597 621 651 790 46000 DISTANCE NM 18 19 20 21 29 21 21 22 24 32 TIME MIN 7 7 7 8 10 8 8 8 8 11 FUEL LB 438 455 473 495 582 480 499 518 543 641 42000 DISTANCE NM 15 16 17 18 23 17 18 19 20 26 TIME M...

Page 863: ...708 737 774 950 46000 DISTANCE NM 23 24 25 26 36 25 27 28 29 41 TIME MIN 9 9 9 9 13 9 10 10 10 14 FUEL LB 523 543 565 592 701 566 589 612 642 764 42000 DISTANCE NM 19 20 21 22 29 21 22 23 24 33 TIME M...

Page 864: ...860 905 1127 46000 DISTANCE NM 28 29 31 33 46 31 32 34 36 51 TIME MIN 10 11 11 11 16 11 12 12 12 17 FUEL LB 611 635 661 693 828 657 683 710 745 896 42000 DISTANCE NM 23 24 25 27 36 26 27 28 29 40 TIME...

Page 865: ...1046 1329 46000 DISTANCE NM 34 36 37 40 57 38 39 41 44 63 TIME MIN 12 13 13 14 19 13 14 14 15 21 FUEL LB 704 732 761 799 967 751 781 813 855 1040 42000 DISTANCE NM 28 29 30 32 44 31 32 33 35 49 TIME...

Page 866: ...1190 1543 46000 DISTANCE NM 41 43 44 48 70 44 46 48 52 77 TIME MIN 14 15 15 16 23 16 16 16 17 25 FUEL LB 798 831 864 910 1116 846 880 915 966 1191 42000 DISTANCE NM 33 35 36 39 54 36 37 39 42 59 TIME...

Page 867: ...DISTANCE NM 48 50 52 56 85 52 54 56 61 94 TIME MIN 17 17 17 18 27 18 18 19 20 29 FUEL LB 894 930 968 1022 1269 944 983 1023 1082 1352 42000 DISTANCE NM 39 40 42 45 64 42 43 45 49 70 TIME MIN 13 14 14...

Page 868: ...CE NM 56 59 61 67 104 62 64 67 73 116 TIME MIN 19 20 20 21 32 21 21 22 23 35 FUEL LB 997 1038 1080 1145 1442 1054 1097 1141 1212 1541 42000 DISTANCE NM 45 47 49 53 76 49 51 53 57 84 TIME MIN 15 16 16...

Page 869: ...STANCE NM 89 92 96 TIME MIN 29 30 30 FUEL LB 1405 1463 1521 1633 46000 DISTANCE NM 68 70 73 81 TIME MIN 22 23 23 25 FUEL LB 1115 1161 1207 1285 1650 42000 DISTANCE NM 53 55 57 62 93 TIME MIN 18 18 18...

Page 870: ...s flown at a speed corresponding to a specific range equal to 99 of the maximum specific range The LRC schedule is used when range is the main factor considered In the Maximum Speed Cruise schedule th...

Page 871: ...70 1356 1344 1335 1325 1313 IAS KT 186 185 184 184 183 182 181 38000 TAS KT 200 202 204 206 208 211 213 INDICATED MACH 0 308 0 312 0 316 0 321 0 326 0 331 0 336 BUFFET MARGIN G 1 98 1 95 1 93 1 91 1 9...

Page 872: ...03 1298 1288 1280 1274 1271 1265 IAS KT 181 180 179 179 178 178 177 38000 TAS KT 215 218 220 223 226 229 232 INDICATED MACH 0 341 0 347 0 352 0 357 0 363 0 369 0 375 BUFFET MARGIN G 1 84 1 83 1 81 1 7...

Page 873: ...G 1260 1257 1257 1254 1253 1253 1254 IAS KT 176 176 175 175 174 173 173 38000 TAS KT 234 237 241 244 247 250 254 INDICATED MACH 0 381 0 388 0 395 0 402 0 408 0 416 0 423 BUFFET MARGIN G 1 74 1 72 1 72...

Page 874: ...FFET MARGIN G 2 54 2 47 2 44 2 40 2 35 2 28 2 24 SR NM LB 0 062 0 063 0 064 0 065 0 067 0 068 0 069 N1 79 1 79 6 80 1 80 6 81 2 81 6 82 0 F FLOW LB H ENG 2024 1993 1968 1942 1917 1885 1856 IAS KT 235...

Page 875: ...97 1973 1947 1923 1892 1864 IAS KT 245 243 242 240 239 237 235 30000 TAS KT 261 263 266 267 270 272 274 INDICATED MACH 0 405 0 409 0 415 0 419 0 425 0 429 0 433 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 5...

Page 876: ...39 BUFFET MARGIN G 2 19 2 13 2 06 2 02 2 03 2 02 1 99 SR NM LB 0 071 0 072 0 074 0 075 0 076 0 077 0 078 N1 82 4 82 7 83 83 3 84 2 85 2 85 9 F FLOW LB H ENG 1828 1795 1761 1731 1748 1759 1751 IAS KT 2...

Page 877: ...1803 1769 1739 1758 1770 1761 IAS KT 233 231 228 226 226 227 226 30000 TAS KT 276 277 278 280 285 291 294 INDICATED MACH 0 438 0 442 0 445 0 449 0 460 0 471 0 478 BUFFET MARGIN G 2 56 2 56 2 56 2 56...

Page 878: ...1727 1705 1678 1647 1628 1599 IAS KT 216 215 213 211 208 206 203 38000 TAS KT 287 290 292 294 294 296 297 INDICATED MACH 0 466 0 473 0 478 0 483 0 485 0 490 0 495 BUFFET MARGIN G 2 56 2 51 2 45 2 39 2...

Page 879: ...ITH LANDING GEAR DOWN The descent table shows fuel consumption distance and time from the top of descent to sea level for various cruise altitudes The data is calculated based on flight idle thrust an...

Page 880: ...5000 10000 15000 20000 25000 FUEL LB 21 42 60 76 90 46000 DISTANCE NM 6 11 17 23 30 TIME MIN 1 3 4 5 6 FUEL LB 20 39 56 72 85 42000 DISTANCE NM 5 11 16 22 28 TIME MIN 1 3 4 5 6 FUEL LB 19 37 53 67 79...

Page 881: ...DING FLIGHT WITH LANDING GEAR DOWN The holding tables show indicated airspeed Mach number N1 fuel flow and fuel consumption for various weights and altitudes Data is presented for ISA condition and al...

Page 882: ...359 2406 IAS KT 166 164 160 155 152 150 150 TAS KT 164 9 166 6 171 0 178 9 189 0 202 3 219 6 38000 MACH 0 250 0 254 0 264 0 282 0 304 0 331 0 367 N1 61 9 62 8 64 9 68 3 71 4 75 8 80 3 FF LB H ENG 1242...

Page 883: ...this case the applicable AFM supplement must be observed for takeoff driftdown and landing performance penalties On board flight planning in case of flaps locked at 9 after takeoff CLIMB FLIGHT WITH F...

Page 884: ...7 9 8 8 8 9 11 TIME MIN 2 2 2 2 3 2 2 3 3 3 FUEL LB 141 146 152 158 177 169 175 182 190 212 42000 DISTANCE NM 6 6 6 6 8 7 7 7 8 10 TIME MIN 2 2 2 2 2 2 2 2 2 3 FUEL LB 123 127 132 138 153 147 153 159...

Page 885: ...1 12 12 16 TIME MIN 3 3 3 3 4 3 3 3 4 5 FUEL LB 197 205 213 222 248 225 234 243 254 285 42000 DISTANCE NM 8 8 9 9 12 9 10 10 11 13 TIME MIN 3 3 3 3 3 3 3 3 3 4 FUEL LB 171 178 185 193 214 196 204 211...

Page 886: ...21 TIME MIN 4 4 4 4 5 4 4 4 5 6 FUEL LB 254 264 274 286 321 282 293 305 318 358 42000 DISTANCE NM 11 11 12 12 15 12 13 13 14 18 TIME MIN 3 3 3 4 4 4 4 4 4 5 FUEL LB 220 229 238 248 276 245 255 265 27...

Page 887: ...ME MIN 5 5 5 5 7 5 5 6 6 7 FUEL LB 311 323 336 351 396 340 353 367 383 434 42000 DISTANCE NM 14 14 15 16 20 15 16 16 17 22 TIME MIN 4 4 4 4 6 5 5 5 5 6 FUEL LB 270 280 291 304 340 294 306 318 332 372...

Page 888: ...N 6 6 6 6 8 6 6 7 7 9 FUEL LB 369 384 399 416 472 398 414 431 450 512 42000 DISTANCE NM 17 18 18 19 25 19 19 20 21 27 TIME MIN 5 5 5 5 7 6 6 6 6 7 FUEL LB 319 332 345 360 404 344 358 372 389 437 38000...

Page 889: ...7 7 7 8 10 8 8 8 8 10 FUEL LB 428 445 463 484 552 458 477 496 518 592 42000 DISTANCE NM 20 21 22 23 30 22 23 24 26 33 TIME MIN 6 6 6 6 8 6 7 7 7 9 FUEL LB 370 385 400 417 471 395 411 428 447 504 38000...

Page 890: ...8 8 9 11 9 9 9 10 12 FUEL LB 489 509 529 553 634 519 540 562 588 676 42000 DISTANCE NM 24 25 26 28 36 26 27 29 30 40 TIME MIN 7 7 7 8 10 8 8 8 8 10 FUEL LB 421 438 456 476 539 447 465 484 506 574 380...

Page 891: ...10 10 13 10 10 10 11 14 FUEL LB 550 572 595 624 718 580 604 628 659 761 42000 DISTANCE NM 28 30 31 33 43 31 32 33 35 46 TIME MIN 8 8 8 9 11 9 9 9 9 12 FUEL LB 473 492 512 536 609 498 519 539 565 644 3...

Page 892: ...own at a speed corresponding to a specific range equal to 99 of the maximum specific range The LRC schedule is used when range is the main factor considered In the Maximum Speed Cruise schedule the ai...

Page 893: ...062 1052 IAS KT 218 217 216 215 214 214 213 212 38000 TAS KT 234 236 239 241 244 247 249 252 INDICATED MACH 0 360 0 366 0 371 0 376 0 382 0 387 0 393 0 399 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 5...

Page 894: ...007 1001 995 IAS KT 211 210 210 209 208 208 207 206 38000 TAS KT 255 258 261 264 268 271 275 278 INDICATED MACH 0 405 0 411 0 418 0 425 0 432 0 439 0 446 0 453 BUFFET MARGIN G 2 51 2 48 2 46 2 44 2 41...

Page 895: ...IAS KT 250 250 250 250 250 250 250 250 38000 TAS KT 268 272 276 280 284 288 292 297 INDICATED MACH 0 413 0 420 0 428 0 436 0 444 0 452 0 461 0 469 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2...

Page 896: ...37 IAS KT 250 250 250 250 250 250 250 250 38000 TAS KT 301 306 311 315 320 325 330 335 INDICATED MACH 0 478 0 487 0 497 0 506 0 516 0 526 0 536 0 547 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56...

Page 897: ...AIRPLANE OPERATIONS MANUAL FLIGHT PLANNING EMB 145 A1 and A1P LB MARCH 28 2002 1 05 40 Page 15 Code 02 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 898: ...FLAPS LOCKED AT 9 The descent table shows fuel consumption distance and time from the top of descent to sea level for various cruise altitudes The data is calculated based on flight idle thrust and a...

Page 899: ...OF DESCENT FT LB 5000 10000 15000 20000 FUEL LB 39 75 107 136 46000 DISTANCE NM 10 20 31 42 TIME MIN 2 5 7 9 FUEL LB 38 72 102 130 42000 DISTANCE NM 9 19 29 40 TIME MIN 2 4 7 9 FUEL LB 36 68 96 123 38...

Page 900: ...FLIGHT WITH FLAPS LOCKED AT 9 The holding tables show indicated airspeed Mach number N1 fuel flow and fuel consumption for various weights and altitudes Data is presented for ISA condition and all en...

Page 901: ...H 2027 1992 1920 1844 1796 1773 IAS KT 166 164 160 155 152 150 TAS KT 164 9 166 6 171 0 178 9 189 0 202 3 38000 MACH 0 250 0 254 0 264 0 282 0 304 0 331 N1 53 1 54 0 56 4 60 3 64 5 68 3 FF LB H ENG 94...

Page 902: ...FLIGHT PLANNING EMB 145 A1 and A1P LB AIRPLANE OPERATIONS MANUAL 1 05 40 Page 20 Code 02 MARCH 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 903: ...point in cruise to an alternate airport The charts also enable rapid determination of fuel and time required to proceed to an alternate airport Fuel and time are determined in the same way as the sim...

Page 904: ...1500 1000 500 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 8500 9000 9500 0 200 400 600 800 1000 1200 1400 1600 145AOM1054506A 22FEB2001 LANDING WEIGHT lb TAIL HEA...

Page 905: ...20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 105 110 115 120 125 130 135 140 145 150 155 160 165 170 175 180 185 190 195 200 205 210 215 220 225 230 235 240 245 250 255 260 0 200 400 600 800 10...

Page 906: ...require that the actual airplane performance be calculated in the most conservative airplane configuration and then further decreased by a 1 1 climb gradient for two engine airplanes This reduced grad...

Page 907: ...ontour maps of the high terrain and plotting the highest points within the corridor s width along the route or alternatively using Minimum En Route Altitude MEA or Minimum Off Route Altitude MORA The...

Page 908: ...profile In case of an emergency descent the airplane path must be at or below the generator profile in order to ensure sufficient supplemental breathing oxygen to the passengers Time min 38000 36000...

Page 909: ...Page 7 Code 06 AOM 145 1114 GENERATOR DESCENT PROFILE 22 MINUTE CHEMICAL OXYGEN 38000 36000 34000 32000 30000 28000 26000 24000 22000 20000 18000 16000 14000 12000 10000 Pressure Altitude ft Time min...

Page 910: ...FLIGHT PLANNING EMB 145 A1 LB FAA AIRPLANE OPERATIONS MANUAL 1 05 45 Page 8 Code 06 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 911: ...de capability and cruise data for flight with all engines operating and the Engine Anti Ice Valve Locked Open according to DDPM procedure 30 21 01 This set of data may be used in the following situati...

Page 912: ...RUISE ALTITUDE CAPABILITY ENGINE ANTI ICE VALVE LOCKED OPEN ALL ENGINES OPERATING AE3007A1 AND A1P ENGINES MAX SPEED CRUISE CRUISE THRUST LIMITED ISA C Weight lb 10 5 0 5 10 15 20 25 30 35 50000 330 3...

Page 913: ...ange It is used when range is the principal factor In the maximum speed schedule the airplane is flown in a speed resulting from maximum cruise power setting It is used when minimum flight time is des...

Page 914: ...2 1 72 6 73 3 73 9 74 6 F FLOW LB H ENG 1375 1348 1334 1320 1307 1298 1284 1275 1264 1255 IAS KT 250 252 251 250 248 247 246 245 243 242 46000 TAS KT 268 291 294 297 300 303 306 310 313 316 INDICATED...

Page 915: ...6 5 67 1 67 6 68 1 68 6 69 2 F FLOW LB H ENG 1203 1116 1101 1087 1073 1060 1045 1033 1021 1011 IAS KT 239 233 232 230 229 228 226 225 224 223 36000 TAS KT 256 268 270 273 276 279 281 284 287 290 INDIC...

Page 916: ...98 0 403 0 408 0 413 0 419 0 425 0 431 0 437 0 443 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 SR NM LB 0 113 0 128 0 132 0 135 0 138 0 142 0 145 0 149 0 152 0 156 N1 56 8 59 4 6...

Page 917: ...79 0 79 7 80 4 81 0 81 7 F FLOW LB H ENG 1247 1240 1233 1229 1224 1218 1214 1210 1209 1207 IAS KT 241 240 238 237 236 235 234 233 233 233 46000 TAS KT 319 323 326 330 333 337 342 346 351 356 INDICATED...

Page 918: ...0 71 6 72 3 73 0 73 7 74 5 75 2 76 0 F FLOW LB H ENG 1000 990 981 972 966 958 952 948 941 938 IAS KT 222 220 219 218 217 216 214 214 212 211 36000 TAS KT 293 296 299 302 306 309 312 316 320 323 INDIC...

Page 919: ...456 0 462 0 469 0 477 0 484 0 491 0 498 0 506 0 513 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 SR NM LB 0 160 0 163 0 167 0 171 0 175 0 178 0 182 0 186 0 189 0 193 N1 64 8 65 3...

Page 920: ...W LB H ENG 1207 1208 1213 1215 1221 1229 1236 1190 IAS KT 232 232 232 232 232 233 233 224 46000 TAS KT 362 367 373 379 386 393 400 392 INDICATED MACH 0 611 0 623 0 636 0 649 0 663 0 679 0 694 0 684 BU...

Page 921: ...6 7 77 5 78 3 78 9 79 6 80 2 80 9 81 6 83 0 F FLOW LB H ENG 932 929 928 926 924 923 923 925 932 IAS KT 209 209 209 208 208 207 207 207 207 36000 TAS KT 326 331 336 342 347 352 357 363 371 INDICATED MA...

Page 922: ...MACH 0 523 0 530 0 538 0 547 0 556 0 567 0 578 0 590 0 601 BUFFET MARGIN G 2 52 2 46 2 40 2 35 2 29 2 25 2 20 2 15 2 09 SR NM LB 0 197 0 200 0 204 0 207 0 210 0 214 0 218 0 222 0 226 N1 70 8 71 5 72...

Page 923: ...6 80 8 82 0 82 5 83 6 F FLOW LB H ENG 1375 1926 1925 1926 1928 1927 1882 1912 1886 1936 IAS KT 250 320 320 320 320 318 314 316 313 317 46000 TAS KT 268 368 373 379 384 388 389 397 399 410 INDICATED MA...

Page 924: ...6 79 4 80 2 81 0 81 9 F FLOW LB H ENG 1270 1809 1805 1803 1803 1803 1804 1807 1810 1815 IAS KT 250 320 320 320 320 320 320 320 320 320 36000 TAS KT 267 366 371 376 382 387 393 399 405 411 INDICATED MA...

Page 925: ...7 0 598 0 608 0 620 0 631 0 643 0 655 0 667 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 SPECIFIC RANGENM LB0 1100 104 0 106 0 108 0 110 0 112 0 113 0 115 0 116 0 118 N1 60 9 74 3...

Page 926: ...4 85 9 85 8 86 7 86 0 86 3 F FLOW LB H ENG 1885 1879 1896 1868 1815 1813 1743 1777 1655 1629 IAS KT 312 311 311 308 303 301 295 298 287 283 46000 TAS KT 410 415 421 423 422 427 425 436 427 428 INDICAT...

Page 927: ...2 85 8 85 6 86 4 85 8 86 1 F FLOW LB H ENG 1821 1828 1836 1845 1850 1852 1777 1803 1687 1656 IAS KT 320 320 320 320 319 319 311 312 302 297 36000 TAS KT 417 423 429 436 441 447 444 452 445 445 INDICAT...

Page 928: ...0 693 0 706 0 719 0 733 0 747 0 761 0 780 0 772 0 777 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 2 56 SR NM LB 0 119 0 121 0 122 0 124 0 125 0 126 0 128 0 128 0 134 0 137 N1 80 9 81...

Page 929: ...LOW LB H ENG 1543 1466 1417 1349 1340 1329 1259 1190 IAS KT 275 266 259 251 249 247 236 224 46000 TAS KT 423 417 414 408 412 416 406 392 INDICATED MACH 0 714 0 707 0 706 0 698 0 708 0 718 0 704 0 684...

Page 930: ...6 85 6 85 4 85 9 86 5 86 3 86 0 85 8 F FLOW LB H ENG 1565 1505 1455 1398 1394 1391 1326 1255 1157 IAS KT 287 282 276 271 270 270 262 254 241 36000 TAS KT 438 437 437 436 442 448 444 439 427 INDICATED...

Page 931: ...ED MACH 0 771 0 774 0 773 0 773 0 780 0 780 0 780 0 780 0 780 BUFFET MARGIN G 2 56 2 56 2 56 2 56 2 56 2 50 2 38 2 27 2 16 SR NM LB 0 143 0 147 0 152 0 158 0 161 0 168 0 174 0 181 0 188 N1 85 3 85 2 8...

Page 932: ...FLIGHT PLANNING EMB 145 A1 and A1P LB AIRPLANE OPERATIONS MANUAL 1 05 50 Page 22 Code 02 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 933: ...AND BALANCE TABLE OF CONTENTS Page Block Introduction 1 06 00 Standard Terms and Definitions 1 06 10 General Data 1 06 15 Index System 1 06 30 Center of Gravity Curtailments 1 06 40 Balance Chart 1 06...

Page 934: ...MANUAL 1 06 00 Page 2 Code 01 REVISION 17 INTRODUCTION This Section contains information equivalent to the Weight and Balance manual and is intended to assist the operator in defining the weight and b...

Page 935: ...ygen fire extinguisher agent landing gear shock absorber fluid etc BASIC EMPTY WEIGHT BEW It is the MEW plus the weight of the following items APU oil Engine oil Hydraulic fluid Unusable fuel OPERATIO...

Page 936: ...ZFW is related to airplane structural limitations MAXIMUM DESIGN RAMP WEIGHT MRW This is the maximum authorized ramp weight MAXIMUM DESIGN TAKEOFF WEIGHT MTOW This is the maximum authorized weight for...

Page 937: ...y rectangular airfoil with the same area of the actual wing and which produces the same resulting force vectors of the actual wing The aircraft forward and aft CG limits are referred to in terms of MA...

Page 938: ...WEIGHT AND BALANCE AIRPLANE OPERATIONS MANUAL 1 06 10 Page 4 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 939: ...02 AOM 145 1114 GENERAL DATA The general data presented in this section is intended to be used for specific weight and balance calculations and is equivalent to the information contained in the Weigh...

Page 940: ...cated at the zero station of the fuselage Balance Arms BA are equivalent to Body Station BS on the EMB 145 models AIRPLANE DATUM The Airplane Datum is a plane perpendicular to the fuselage centerline...

Page 941: ...cated at the zero station of the fuselage Balance Arms BA are equivalent to Body Station BS on the ERJ 140 ER and LR models AIRPLANE DATUM The Airplane Datum is a plane perpendicular to the fuselage c...

Page 942: ...cated at the zero station of the fuselage Balance Arms BA are equivalent to Body Station BS on the EMB 135 ER and LR models AIRPLANE DATUM The Airplane Datum is a plane perpendicular to the fuselage c...

Page 943: ...not be drawn off by standard draining procedures FUEL QUANTITIES EMB 145 MODELS EMB 145 ER EP and MP Models FUEL CATEGORY VOLUME US Gal WEIGHT lb CG BALANCE ARM in UNUSABLE UNDRAINABLE 1 6 11 580 31...

Page 944: ...57 Ventral Tank FUEL CATEGORY VOLUME US Gal WEIGHT lb CG BALANCE ARM in UNUSABLE UNDRAINABLE 0 7 5 0 678 43 UNUSABLE DRAINABLE 2 4 16 1 680 63 TOTAL UNUSABLE 3 1 21 1 680 91 USABLE 275 3 1862 7 696 3...

Page 945: ...adopted fuel density of 6 767 lb US Gal FUEL QUANTITIES EMB 135 MODELS EMB 135 ER Model FUEL CATEGORY VOLUME US Gal WEIGHT lb CG BALANCE ARM in UNUSABLE UNDRAINABLE 1 6 11 501 34 UNUSABLE DRAINABLE 12...

Page 946: ...GHT lb BALANCE ARM in ENGINE OIL 1 53 0 823 43 APU OIL 1 4 4 1014 76 HYDRAULIC 2 WITH THRUST REVERSER 75 0 699 2 WITHOUT THRUST REVERSER 68 3 684 2 LAVATORY CHEMICAL FLUID 15 4 754 13 LAVATORY RINSE W...

Page 947: ...rimming immediately when the value 4 is displayed EMB 145 MODELS CG POSITION LESS THAN OR EQUAL TO 27 5 27 6 UP TO 32 5 32 6 UP TO 36 5 36 6 UP TO 41 5 ABOVE OR EQUAL TO 41 6 PITCH TRIM UNITS 8 7 6 5...

Page 948: ...135 LB AIRPLANE OPERATIONS MANUAL 1 06 15 Page 10 Code 02 REVISION 37 AOM 145 1114 PASSENGERS PASSENGER LOCATION The passenger location and respective balance arm are shown in the applicable Interior...

Page 949: ...assenger or by asking each passenger their weight and adding there to a predetermined constant to compensate the handcarried articles and clothing According to AC 120 27E the following standard averag...

Page 950: ...ITEM WEIGHT lb BALANCE ARM in PILOT 190 145 08 COPILOT 190 145 08 OBSERVER 190 167 64 FWD ATTENDANT 170 185 00 AFT ATTENDANT 170 787 44 PILOT FLIGHT BAG 20 152 87 ERJ 140 MODELS ITEM WEIGHT lb BALANC...

Page 951: ...646 46 PILOT FLIGHT BAG 20 152 87 NOTE The adopted flight crew items are in accordance with the approved average weight not including the respective carry on baggage The crewmembers and attendants we...

Page 952: ...WEIGHT AND BALANCE 145 140 135 LB AIRPLANE OPERATIONS MANUAL 1 06 15 Page 14 Code 02 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 953: ...ntion for presenting aircraft or body moments on a different measuring system When using the Index System short numeric expressions result The Index System formula is presented below C B A Arm W I whe...

Page 954: ...17400 550 Arm W I EMB 135 Models 13 17400 515 Arm W I INDEX INFLUENCE Index influence is the variation of index when a body is loaded or unloaded from the aircraft It is usually referred in index uni...

Page 955: ...99 IU Cockpit Observer 165 35 190 4 64 IU Pax Cabin A 338 98 190 2 74 IU Pax Pax Cabin B 508 66 190 0 89 IU Pax Pax Cabin C 702 36 190 1 23 IU Pax The galley and wardrobe arms are for the standard co...

Page 956: ...abin C 654 02 190 1 14 IU Pax The galley and wardrobe arms are for the standard configuration Check the airplane actual configuration arms in the AOM Loading Section For the purposes of this table the...

Page 957: ...ley and wardrobe arms are for the option 1 configuration Check the airplane actual configuration arms in the AOM Loading Section For the purposes of this table the passenger cabin was divided in three...

Page 958: ...1 0 350 2345 582 52 1 0 400 2680 583 35 1 0 450 3015 584 17 1 0 500 3350 585 04 1 0 550 3685 585 91 0 9 600 4020 586 81 0 7 650 4355 587 68 0 6 700 4690 588 54 0 4 750 5025 589 37 0 2 800 5360 590 20...

Page 959: ...77 2 5 550 3685 577 33 2 7 600 4020 577 89 2 8 650 4355 578 44 2 9 700 4690 579 00 3 0 750 5025 579 66 3 0 800 5360 580 22 3 0 850 5695 580 89 3 0 900 6030 581 55 2 9 950 6365 582 12 2 9 1000 6700 582...

Page 960: ...576 77 2 5 550 3685 577 33 2 7 600 4020 577 89 2 8 650 4355 578 44 2 9 700 4690 579 00 3 0 750 5025 579 66 3 0 800 5360 580 22 3 0 850 5695 580 89 3 0 900 6030 581 55 2 9 950 6365 582 12 2 9 1000 670...

Page 961: ...ral Tank Volume Weight Arm Index US Gal lb in IU 100 670 689 17 3 8 200 1340 691 73 7 8 300 2010 693 78 12 0 400 2680 696 38 16 4 500 3350 696 85 20 6 600 4020 697 72 24 9 700 4690 698 31 29 2 800 536...

Page 962: ...49 0 5 400 2680 547 34 0 4 450 3015 548 16 0 3 500 3350 549 00 0 2 550 3685 549 87 0 0 600 4020 550 77 0 2 650 4355 551 65 0 4 700 4690 552 51 0 7 750 5025 553 36 1 0 800 5360 554 17 1 3 850 5695 554...

Page 963: ...1 8 550 3685 541 28 1 8 600 4020 541 86 1 9 650 4355 542 43 1 9 700 4690 543 03 1 9 750 5025 543 62 1 8 800 5360 544 23 1 8 850 5695 544 90 1 7 900 6030 545 53 1 5 950 6365 546 13 1 4 1000 6700 546 76...

Page 964: ...54 1 5 400 2680 504 39 1 6 450 3015 505 21 1 7 500 3350 506 05 1 7 550 3685 506 92 1 7 600 4020 507 82 1 7 650 4355 508 70 1 6 700 4690 509 56 1 5 750 5025 510 41 1 3 800 5360 511 22 1 2 850 5695 512...

Page 965: ...3 3 550 3685 498 33 3 5 600 4020 498 91 3 7 650 4355 499 48 3 9 700 4690 500 08 4 0 750 5025 500 67 4 1 800 5360 501 28 4 2 850 5695 501 95 4 3 900 6030 502 58 4 3 950 6365 503 18 4 3 1000 6700 503 81...

Page 966: ...Item Weight lb Arm in Moment lb in BEW 26572 16546149 55 Lavatory fluid 44 15 43 813 38 810 24 35788 72 12502 00 Pilot Co Pilot 380 142 91 54305 80 Flight attendant fwd 170 188 97 32124 90 CREWMEMBER...

Page 967: ...ations that affect the CG position for takeoff and landing Uneven distribution of passengers flap and landing gear movement and cargo baggage shift are considered takeoff and landing allowances Flight...

Page 968: ...r of gravity envelope without the seat allowances may be used so as not to limit these types of flight unnecessarily FLAP MOVEMENT ALLOWANCES Flap movement has negligible effects on the airplane Cente...

Page 969: ...attendant and a trolley to the aftermost row combined with the movement of a mid cabin passenger to the lavatory Example EMB 135ER Aft Allowance Weight lb from Arm in to Arm in Moment lb in Mid cabin...

Page 970: ...ation in passenger seating locations Manual load sheets usually use the Cabin Area Trim method where passengers are considered evenly distributed along the passenger cabin thus requiring seating allow...

Page 971: ...e between the actual pax distribution moment and the moment of the same amount of passengers concentrated in the centroid of the cabin zone considered NOTE Seating allowance does not need to be consid...

Page 972: ...e idea is to determine a constrained ZFW envelope in which the fuel loading curve is always located inside the CG envelope CONSTRAINED CENTER OF GRAVITY LIMITS In order to determine the constrained CG...

Page 973: ...d and row 1 centroid When window row 2 is occupied the moment margin is increased by the passenger weight times the distance between cabin A centroid and row 2 centroid The moment margin keeps increas...

Page 974: ...12560 92 37009 91 Windows 07 448 78 450 59 380 2 687 94 37697 85 Windows 08 480 02 450 59 380 2 11185 04 26512 80 Windows 09 520 36 450 59 380 2 26512 80 0 00 Aisle 05 386 25 450 59 190 1 12224 49 12...

Page 975: ...450 59 380 2 26512 80 26512 80 Windows 8 480 02 450 59 380 2 11185 04 37697 85 Windows 7 448 78 450 59 380 2 687 94 37009 91 Windows 6 417 54 450 59 380 2 12560 92 24448 99 Windows 5 386 25 450 59 38...

Page 976: ...44000 46000 48000 10 20 30 40 50 60 70 INDEX WEIGHT lb a a 20 25 30 40 35 TOW ZFW Figure 1 In order to prevent the LW CG from being located outside of the CG envelope the idea is to determine a constr...

Page 977: ...8 9 35274 514 44 16 5 11 9 44092 519 63 21 1 24 7 Aft limits Weight Arm CG Index lb in IU 25353 529 67 30 0 34 3 26455 538 69 38 0 48 8 35274 538 69 38 0 60 8 44092 538 69 38 0 72 7 Drawing the fuel i...

Page 978: ...ope The table below shows the determination of the forward constrained limit for the EMB 135LR model For Takeoff Landing In flight limits the allowance used was 10155 15 lb in landing gear 4017 00 lb...

Page 979: ...use of the existence of more limiting points at the same weight The table below shows the determination of the aft constrained limit for the EMB 135LR model For Takeoff Landing In flight limits the al...

Page 980: ...PERATIONS MANUAL 1 06 40 Page 14 Code 03 REVISION 29 EMB 135LR CONSTRAINED ENVELOPE 25000 30000 35000 40000 45000 15 20 25 30 35 40 CG WEIGHT lb Figure 3 The complete constrained CG envelope for the E...

Page 981: ...nstrained CG Envelope Standard 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 0 10 20 30 40 50 60 70 INDEX WEIGHT lb a a 15 20 25 30 40 1 2 MTOW 19990 lb MLW 18500 lb MZFW 160...

Page 982: ...is occupied the moment margin is increased by the passenger weight times the distance between cabin A centroid and row 2 centroid The moment margin keeps increasing until the seats aft of the cabin c...

Page 983: ...98 Windows 10 527 23 513 10 380 2 5370 75 49815 23 Windows 11 558 47 513 10 380 2 17243 73 32571 49 Windows 12 598 81 513 10 380 2 32571 49 0 00 Aisle 07 433 42 513 10 190 1 15139 18 15139 18 55185 98...

Page 984: ...ndows 11 558 47 513 10 380 2 17243 73 49815 23 Windows 10 527 23 513 10 380 2 5370 75 55185 98 Windows 09 495 94 513 10 380 2 6517 32 48668 66 Windows 08 464 70 513 10 380 2 18390 30 30278 36 Windows...

Page 985: ...48000 50000 52000 10 20 30 40 50 60 70 80 90 INDEX WEIGHT lb a a 15 20 25 40 35 30 45 ZFW TOW Figure 1 In order to prevent the LW CG from being located outside of the CG envelope the idea is to determ...

Page 986: ...12 0 9 4 48501 595 56 18 4 28 5 Aft limits Weight Arm CG Index lb in IU 27337 608 64 30 0 42 3 29542 623 30 43 0 69 5 34170 623 30 43 0 78 4 38000 619 36 39 5 77 1 48501 619 36 39 5 94 8 Drawing the...

Page 987: ...velope The table below shows the determination of the forward constrained limit for the EMB 145LR For Takeoff Landing In flight limits the allowance used was 10155 15 lb in landing gear 4017 00 lb in...

Page 988: ...f more limiting points at the same weight The table below shows the determination of the aft constrained limit for the EMB 145LR For Takeoff Landing In flight limits the allowance used was 192360 00 l...

Page 989: ...AND BALANCE REVISION 29 1 06 40 Page 23 Code 03 EMB 145LR CONSTRAINED ENVELOPE 25000 30000 35000 40000 45000 50000 10 15 20 25 30 35 40 CG WEIGHT lb Figure 3 The complete constrained CG envelope for t...

Page 990: ...d CG Envelope 26000 28000 30000 32000 34000 36000 38000 40000 42000 44000 46000 48000 50000 52000 0 10 20 30 40 50 60 70 80 90 INDEX WEIGHT lb a a 10 15 20 25 40 1 2 MTOW 48501 lb MLW 42549 lb MZFW 39...

Page 991: ...ample shown in the next page is a diagram format balance chart In order to use it the following steps must be followed 1 Enter the aircraft OEI in the Basic Index scale 2 Write the wardrobe WRDB cargo...

Page 992: ...CG envelope until it crosses a horizontal line at the TOW The crossing point determines the TOW CG and if it is located outside of the TOW envelope a new loading distribution must be made 9 Enter the...

Page 993: ...AIRPLANE OPERATIONS MANUAL WEIGHT AND BALANCE JUNE 28 2002 1 06 50 Page 3 Code 01 SAMPLE EMB 145 EP BALANCE CHART...

Page 994: ...WEIGHT AND BALANCE AIRPLANE OPERATIONS MANUAL 1 06 50 Page 4 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 995: ...CTION 1 07 LOADING Introduction 1 07 00 External Dimensions 1 07 10 Cabin Cross Section 1 07 20 Interior Arrangement 1 07 30 Carry on baggage 1 07 50 Baggage Door 1 07 60 Baggage Compartment 1 07 70 C...

Page 996: ...This Section contains airplane dimensions interior arrangement data for loading purposes and loading capacity information in the passenger cabin and baggage compartment Instructions for loading and u...

Page 997: ...AIRPLANE OPERATIONS MANUAL LOADING REVISION 23 1 07 10 Page 1 Code 40 EXTERNAL DIMENSIONS EMB 145 THREE VIEW DRAWING...

Page 998: ...in Main Door Open 1st step 0 480 m 1 ft 7 in 0 360 m 1 ft 2 in Service Door 1 595 m 5 ft 3 in 1 408 m 4 ft 7 in Main Landing Gear Door 0 471 m 1 ft 6 in 0 398 m 1 ft 3 in Nacelle 2 425 m 7 ft 11 in 2...

Page 999: ...AIRPLANE OPERATIONS MANUAL LOADING MARCH 30 2001 1 07 10 Page 3 Code 40 EMB 145 DOOR CLEARANCES 145APM020052...

Page 1000: ...LOADING AIRPLANE OPERATIONS MANUAL 1 07 10 Page 4 Code 40 JUNE 28 2002 EMB 145 DOOR CLEARANCES...

Page 1001: ...AIRPLANE OPERATIONS MANUAL LOADING SEPTEMBER 20 1999 1 07 20 Page 1 Code 01 CABIN CROSS SECTION...

Page 1002: ...LOADING AIRPLANE OPERATIONS MANUAL 1 07 20 Page 2 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1003: ...07 30 Page 1 Code 41 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 1A W Wardrobe S Stowage Compartment C Forward Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G Af...

Page 1004: ...7 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19 100 751 97 18 48 49 50 1...

Page 1005: ...07 30 Page 1 Code 42 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 2 A Wardrobe B Stowage Compartment C Forward Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G Aft...

Page 1006: ...97 10 24 25 26 13 411 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19...

Page 1007: ...7 30 Page 1 Code 43 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 3 A Outboard Galley B Stowage Compartment C Fwd Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G A...

Page 1008: ...7 10 24 25 26 13 411 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19 1...

Page 1009: ...37 1 07 30 Page 1 Code 44 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 4 A Forward Galley B Wardrobe C Mid Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G Aft Fli...

Page 1010: ...496 97 10 24 25 26 13 410 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 950 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 312 720 98 17 45 46 4...

Page 1011: ...38 1 07 30 Page 1 Code 45 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 5 A Forward Galley B Wardrobe C Mid Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G Aft Fli...

Page 1012: ...0 24 25 26 13 410 527 99 11 27 28 29 14 197 558 98 12 30 31 32 15 162 596 97 13 33 34 35 15 950 627 99 14 36 37 38 16 737 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 312 720 98 17 45 46 47 19 099...

Page 1013: ...Code 46 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 6 A Wardrobe B Stowage Compartment C Forward Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G Aft Flight Atte...

Page 1014: ...11 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19 100 751 97 18 48 49...

Page 1015: ...98 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19 100 751 97 18 48 49 50 19 888 782 99 NOTE Pas...

Page 1016: ...8 1 07 30 Page 1 Code 47 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 STD CONFIGURATION A Wardrobe B Stowage Unit C Stowage Compartment D Aft Galley E Forward Flight Attendant F Cockpit Observer G Aft Fl...

Page 1017: ...0 24 25 26 13 411 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19 100...

Page 1018: ...LOADING REVISION 26 1 07 30 Page 1 Code 48 INTERIOR ARRANGEMENT EMB 145 BAF CORPORATE CONFIGURATION A Galley B Flight Attendant Seat C Cockpit Observer D Baggage Compartment E G Double Table F H Singl...

Page 1019: ...13 280 522 83 6 16 17 18 14 067 553 82 7 19 20 21 15 083 593 82 8 22 23 24 15 870 624 80 9 25 26 27 16 658 655 83 10 28 29 30 17 445 686 81 11 31 32 33 18 233 717 84 12 34 35 36 19 020 748 82 13 37 38...

Page 1020: ...S MANUAL LOADING REVISION 26 1 07 30 Page 3 Code 48 EMB 145 BAF SECOND CORPORATE CONFIGURATION A Galley B Flight Attendant Seat C Cockpit Observer D Baggage Compartment E Double Table F Single Table W...

Page 1021: ...1 81 6 16 17 18 13 280 522 83 7 19 20 21 14 067 553 82 8 22 23 24 15 083 593 82 9 25 26 27 15 870 624 80 10 28 29 30 16 658 655 83 11 31 32 33 17 445 686 81 12 34 35 36 18 233 717 84 13 37 38 39 19 02...

Page 1022: ...OPERATIONS MANUAL LOADING REVISION 26 1 07 30 Page 1 Code 49 INTERIOR ARRANGEMENT EMB 145 BAF SHUTTLE CONFIGURATION A Galley B Flight Attendant Seat C Cockpit Observer D Baggage Compartment W Wardrobe...

Page 1023: ...460 83 8 20 21 22 12 492 491 81 9 23 24 25 13 280 522 83 10 26 27 28 14 067 553 82 11 29 30 31 15 083 593 82 12 32 33 34 15 870 624 80 13 35 36 37 16 658 655 83 14 38 39 40 17 445 686 81 15 41 42 43 1...

Page 1024: ...NS MANUAL LOADING REVISION 26 1 07 30 Page 1 Code 50 INTERIOR ARRANGEMENT EMB 145 BAF MEDEVAC CONFIGURATION A Galley B Flight Attendant Seat C Cockpit Observer D Baggage Compartment E F G Stretcher W...

Page 1025: ...80 5 13 14 15 16 658 655 83 6 16 17 18 17 445 686 81 7 19 20 21 18 233 717 84 8 22 23 24 19 020 748 82 9 25 26 27 19 807 779 80 PASSENGER AVERAGE CG 16 607 m 653 819 in STRETCHER BALANCE ARM m in E 8...

Page 1026: ...OPERATIONS MANUAL LOADING REVISION 26 1 07 30 Page 3 Code 50 EMB 145 BAF SECOND MEDEVAC CONFIGURATION A Galley B Flight Attendant Seat C Cockpit Observer D Baggage Compartment E Stretcher W Wardrobe...

Page 1027: ...67 553 82 6 16 17 18 15 083 593 82 7 19 20 21 15 870 624 80 8 22 23 24 16 658 655 83 9 25 26 27 17 445 686 81 10 28 29 30 18 233 717 84 11 31 32 33 19 020 748 82 12 34 35 36 19 807 779 80 PASSENGER AV...

Page 1028: ...1 07 30 Page 1 Code 61 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 4A A Outboard Galley B Wardrobe C Forward Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G Aft...

Page 1029: ...97 10 24 25 26 13 410 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 950 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 312 720 98 17 45 46 47 19...

Page 1030: ...07 30 Page 1 Code 70 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 1 W Wardrobe S Stowage Compartment C Forward Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G Aft...

Page 1031: ...411 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19 100 751 97 18 48 4...

Page 1032: ...ON 36 1 07 30 Page 3 Code 70 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145XR CONFIGURATION A Wardrobe B Forward Galley C Aft Galley D Forward Flight Attendant E Stowage Compartment F Aft Flight Attendant...

Page 1033: ...27 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19 100 751 97 18 48 49 50...

Page 1034: ...8 1 07 30 Page 1 Code 71 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 1B A Wardrobe B Forward Galley C Aft Galley D Forward Flight Attendant E Stowage Compartment F Aft Flight Attend...

Page 1035: ...97 10 24 25 26 13 411 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19...

Page 1036: ...0 Page 1 Code 72 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION XZ A Outboard Galley B Stowage Compartment C Forward Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G...

Page 1037: ...97 10 24 25 26 13 411 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 19...

Page 1038: ...0 Page 1 Code 73 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION CZ A Outboard Galley B Stowage Compartment C Forward Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G...

Page 1039: ...6 97 10 24 25 26 13 411 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 951 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 313 720 98 17 45 46 47 1...

Page 1040: ...ode 74 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION FAB VIP A RH Wardrobe B Fwd Galley Catering C Aft Galley Catering D LH Double Wardrobe E LH Stowage F RH Stowage G Baggage Compartment H Cockpit Obser...

Page 1041: ...25 26 27 17 525 689 96 11 28 29 30 18 313 720 98 12 31 32 33 19 100 751 97 13 34 35 36 19 888 782 99 PASSENGER AVERAGE CG 15 030 m 591 73 in Balance Arm m in Volume m 3 cu ft Capacity kg lb RH WARDROB...

Page 1042: ...e 75 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 6A A RH Wardrobe B Forward Galley Catering C Aft Galley Catering D Observer Seat E 1 st Attendant F Emergency Equipment Unit G Lavat...

Page 1043: ...10C 13 411 527 99 11 11A 11B 11C 14 198 558 98 12 12A 12B 12C 15 163 596 97 13 13A 13B 13C 15 951 627 99 14 14A 14B 14C 16 738 658 98 15 15A 15B 15C 17 525 689 96 16 16A 16B 16C 18 313 720 98 17 17A 1...

Page 1044: ...07 30 Page 1 Code 76 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 7 A Wardrobe B Stowage Compartment C Forward Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G Aft...

Page 1045: ...10D 10F 13 411 527 99 11 11A 11D 11F 14 198 558 98 12 12A 12D 12F 15 163 596 97 13 13A 13D 13F 15 951 627 99 14 14A 14D 14F 16 738 658 98 15 15A 15D 15F 17 525 689 96 16 16A 16D 16F 18 313 720 98 17 1...

Page 1046: ...ION 8 1 2 B C D E F G 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 A EM145AOM070030B DGN A Outboard Galley B...

Page 1047: ...12 492 491 81 10 24 25 26 13 280 522 83 11 27 28 29 14 067 553 82 12 30 31 32 15 134 593 82 13 33 34 35 15 895 624 80 14 36 37 38 16 658 655 83 15 39 40 41 17 445 686 81 16 42 43 44 18 223 717 84 17...

Page 1048: ...07 30 Page 1 Code 81 AOM 145 1114 INTERIOR ARRANGEMENT EMB 145 CONFIGURATION OPTION 4B A Wardrobe B Stowage Compartment C Forward Galley D Aft Galley E Forward Flight Attendant F Cockpit Observer G Af...

Page 1049: ...21 22 23 12 623 496 97 10 24 25 26 13 410 527 99 11 27 28 29 14 198 558 98 12 30 31 32 15 163 596 97 13 33 34 35 15 950 627 99 14 36 37 38 16 738 658 98 15 39 40 41 17 525 689 96 16 42 43 44 18 312 7...

Page 1050: ...NS The overhead bins comprise 10 standard overhead bin assemblies and 1 short overhead bin assembly for EMB 145 models 9 standard overhead assemblies and 1 short for ERJ 140 models and 8 standard over...

Page 1051: ...NUAL 1 07 50 Page 2 Code 01 REVISION 25 OVERHEAD BIN CAPACITY AND LENGTH Length m in Capacity kg lb Standard Assembly 1 16 45 67 27 60 Short Assembly 0 83 32 68 20 45 Very Short Assembly 0 49 19 29 14...

Page 1052: ...ter 39 in wide and 1 11 meters 44 in high The baggage door is manually operated from the outside The initial opening movement displacement of the door inward and final closing and latching movement di...

Page 1053: ...LOADING AIRPLANE OPERATIONS MANUAL 1 07 60 Page 2 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1054: ...ated by passenger cabin air flowing into it the baggage ventilation system provides an adequate environment for carrying live animals in the compartment EMB 145 airplanes with a class D baggage compar...

Page 1055: ...ING AIRPLANE OPERATIONS MANUAL 1 07 70 Page 2 Code 01 REVISION 37 AOM 145 1114 DIMENSIONS AND LIMITS Baggage Compartment Balance Arm m in EMB 145 22 601 889 80 ERJ 140 21 186 834 09 EMB 135 19 061 750...

Page 1056: ...140 EMB 135 A Forward Division Position 20 97 825 59 19 55 769 88 17 42 685 83 B Forward Vertical Net 21 78 857 48 20 36 801 77 18 23 717 72 C Aft Vertical Net 23 25 915 35 21 83 859 64 19 70 775 59...

Page 1057: ...Load 390 kg m2 80 lb ft2 Total Maximum Capacity 1200 kg 2646 lb Maximum Capacity per Section 400 kg 882 lb ERJ 140 Compartment Limits Baggage Compartment Available Volume 9 2 m3 325 cu ft Maximum Flo...

Page 1058: ...152 4 114 3 8 104 97 95 90 85 75 60 45 20 32 264 16 246 38 241 3 228 6 215 9 190 5 152 4 114 3 10 104 97 95 90 85 75 60 45 25 4 264 16 246 38 241 3 228 6 215 9 190 5 152 4 114 3 13 104 97 95 90 85 75...

Page 1059: ...ystems as a result of shifting under operational loads Sharp edges like wooden or metal containers or dense cargo objects significantly more dense than typical passenger baggage must be placed under t...

Page 1060: ...EVISION 37 1 07 70 Page 7 Code 01 AOM 145 1114 Before loading or unloading the baggage compartment the Cargo Loading Unloading Ramp also known as Door Jamb Barrier must be lowered in order to protect...

Page 1061: ...LOADING AIRPLANE OPERATIONS MANUAL 1 07 70 Page 8 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 1062: ...ment Smoke Detection System x Baggage Compartment Fire Extinguishing System x Baggage Compartment Ventilation System Although no dedicated temperature control is available the class C baggage compartm...

Page 1063: ...LOADING AIRPLANE OPERATIONS MANUAL 1 07 70 Page 2 Code 02 REVISION 38 AOM 145 1114 DIMENSIONS AND LIMITS EM145AOM071017A DGN 1 70 m 1 50 m 1 10 m 1 10 m 1 25 m 3 34 m 1 53 m...

Page 1064: ...oor Distributed Load 390 kg m2 80 lb ft2 Baggage Compartment Capacity 1000 kg 2205 lb Baggage Compartment Balance Arm 22 85 m 900 in Cart Stowage Unit Capacity 120 kg 265 lb Cart Stowage Unit Balance...

Page 1065: ...60 45 12 7 264 16 246 38 241 3 228 6 215 9 190 5 152 4 114 3 8 104 97 95 90 85 75 60 45 20 32 264 16 246 38 241 3 228 6 215 9 190 5 152 4 114 3 10 104 97 95 90 85 75 60 45 25 4 264 16 246 38 241 3 228...

Page 1066: ...come a hazard to the airplane structure or systems as a result of shifting under operational loads Sharp edges like wooden or metal containers or dense cargo objects significantly more dense than typi...

Page 1067: ...VISION 38 AOM 145 1114 Before loading or unloading the baggage compartment the Cargo Loading Unloading Ramp also known as Door Jamb Barrier must be lowered in order to protect the baggage door latchin...

Page 1068: ...net beam assembly The net beam assembly is attached to an upper attach bracket A cargo net adapter attaches the cargo door safety net to the upper attach bracket Decals on the net assembly indicate o...

Page 1069: ...LOADING AIRPLANE OPERATIONS MANUAL 1 07 80 Page 2 Code 01 DECEMBER 20 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1070: ...AIRPLANE OPERATIONS MANUAL LOADING DECEMBER 20 2002 1 07 80 Page 3 Code 01...

Page 1071: ...planes are equipped with retaining strips located at the upside of the baggage compartment which are used to hold the net while the baggage is placed under it Decals on the cargo net assembly indicate...

Page 1072: ...AIRPLANE OPERATIONS MANUAL LOADING DECEMBER 20 2002 1 07 80 Page 5 Code 01...

Page 1073: ...hree areas and provides horizontal restraint The vertical net is solely intended to optimize the cargo compartment loading The cargo barrier net attaches to the cargo compartment floor with six anchor...

Page 1074: ...AIRPLANE OPERATIONS MANUAL LOADING DECEMBER 20 2002 1 07 80 Page 7 Code 01...

Page 1075: ...LOADING AIRPLANE OPERATIONS MANUAL 1 07 80 Page 8 Code 01 DECEMBER 20 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1076: ...perature control and protected from noise and draught The adverse climatic conditions could cause additional stress to the animals The ambient should be dark to make the animals more calm and comforta...

Page 1077: ...Carbon Dioxide concentration and Humidity that are a result of animal metabolism These items have to be compensated with the baggage compartment ventilation system that draws air from passenger cabin...

Page 1078: ...animals This kind of animal is very susceptible to high and low temperatures It may be necessary to avoid flights at high temperatures during the day and schedule the shipment to night flights In cas...

Page 1079: ...Birds Load Mass kg Load 0 03 3000 0 10 1000 0 25 400 0 50 200 1 00 100 2 50 80 3 OTHERS For the other animals not mentioned in this section estimations could be developed considering the data presente...

Page 1080: ...g that the cargo ventilation system is running properly If this condition is not met avoid storing dry ice on airplanes for extended periods of time Similar precautions must be followed when entering...

Page 1081: ...t an emergency descent to FL 100 to allow activate the emergency ram air ventilation It is also necessary to alert personnel for symptoms of excessive CO2 gas concentrations when around dry ice LOAD L...

Page 1082: ...00 ATA Chapter 06 Dimensions and Areas 1 08 06 ATA Chapter 23 Communications 1 08 23 ATA Chapter 28 Fuel 1 08 28 ATA Chapter 32 Landing Gear 1 08 32 ATA Chapter 33 Lights 1 08 33 ATA Chapter 49 Auxil...

Page 1083: ...notation covering the missing part s on each flight If an additional part is lost the airplane may not depart the airport at which it landed following this event until it complies with the limitation...

Page 1084: ...eoff weight to ensure compliance with the noise requirements Landing performance penalties should be applied to the landing weights that are limited by performance considerations i e landing field len...

Page 1085: ...he identification of the service areas or components MAJOR ZONE AREA 100 Lower fuselage below the floor line 200 Upper fuselage above the floor line 300 Tail cone and empennage group 400 Powerplant an...

Page 1086: ...ound Air Conditioning Connection Access Door 191AR Figures 3 5 1 0 May be missing provided maximum airspeed is limited to 250 KIAS 0 65 M whichever is lower 41 4 Air Conditioning Heat Exchanger Grills...

Page 1087: ...9 Fuel Tank Drain Valve Access Door 192CL Figure 2 4 192DR Figure 3 5 2 0 May be missing provided maximum airspeed is limited to 250 KIAS 0 65 M whichever is lower 41 10 Fuel Wing Stub Drain Valve Ac...

Page 1088: ...whichever is lower 42 1 Pressure Fueling Panel Access Door 191BR Figures 3 5 1 0 May be missing provided a Door microswitch is locked actuated simulating door closed b Refueling defueling and power sw...

Page 1089: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 06 Page 4 Code 01 REVISION 36 AOM 145 1114 FIGURE 1...

Page 1090: ...8 06 Page 5 Code 01 AOM 145 1114 EM145AOM000089A DGN 191EL 191CL 191GL 191KL 191HL 191ML 195AL 195BL 192AL 195CL 193BL 193AL 192EL 193LL 193DL 193FL 193EL 192CL 1 C 2 C 2 C 8 S 6 S 13 S 10 S 8 S 6 S 1...

Page 1091: ...Page 6 Code 01 REVISION 36 AOM 145 1114 191DR 191LR 194BR 194AR 192BR 192DR 194CR 193CR 193MR 193HR 193GR 191JR 191NR 191FR 193JR 8 S 2 C 1 C 1 C 8 S 6 S 13 S 6 S 8 S 2 C 36 S 1 C 20 S 10 S 30 S 5 C 4...

Page 1092: ...AIRPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 36 1 08 06 Page 7 Code 01 AOM 145 1114 FIGURE 4 EMB 145XR...

Page 1093: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 06 Page 8 Code 01 REVISION 36 AOM 145 1114 FIGURE 5 EMB 145XR...

Page 1094: ...g with no penalty 42 6 Maintenance Interphone Connection Door 272BR Figure 6 1 0 May be missing with no penalty 42 7 APU Tail Cone Attaching Bolt Access Door 313GR DR AL BL Figure 6 4 0 May be missing...

Page 1095: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 06 Page 10 Code 01 REVISION 36 AOM 145 1114 FIGURE 6...

Page 1096: ...f 9 nine static dischargers may be missing with no penalty At least the following dischargers are required to be installed a 3 three are installed on each wing b 1 one is installed on the rudder c 3 t...

Page 1097: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 23 Page 2 Code 02 REVISION 39 AOM 145 1114 FIGURE 7...

Page 1098: ...patch Number 4 Remarks and or exceptions 28 FUEL 11 1 Fuel Tank Drain Access Door 192CL Figures 2 4 192DR Figures 3 5 2 0 May be missing provided maximum airspeed is limited to 250 KIAS 0 65 M whichev...

Page 1099: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 28 Page 2 Code 01 REVISION 36 AOM 145 1114 FIGURE 8...

Page 1100: ...AIRPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 36 1 08 28 Page 3 Code 01 AOM 145 1114 FIGURE 9...

Page 1101: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 28 Page 4 Code 01 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 1102: ...M 3 Number required for dispatch Number 4 Remarks and or exceptions 32 LANDING GEAR 10 1 Main Landing Gear Doors Figure 10 2 0 May be missing provided maximum airspeed is limited to 250 KIAS M 0 65 wh...

Page 1103: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 32 Page 2 Code 01 REVISION 27 FIGURE 10...

Page 1104: ...ctive Lens Figure 12 All except EMB 145XR 3 0 May be missing with no penalty Refer to MMEL 33 43 00 43 2 Navigation Light Protective Lens Figure 13 EMB 145 XR 6 0 May be missing with no penalty Refer...

Page 1105: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 33 Page 2 Code 01 REVISION 40 AOM 145 1114 FIGURE 11...

Page 1106: ...AIRPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 40 1 08 33 Page 3 Code 01 AOM 145 1114 FIGURE 12...

Page 1107: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 33 Page 4 Code 01 REVISION 40 AOM 145 1114 FIGURE 13...

Page 1108: ...AIRPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 40 1 08 33 Page 5 Code 01 AOM 145 1114 FIGURE 14...

Page 1109: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 33 Page 6 Code 01 REVISION 40 AOM 145 1114 FIGURE 15...

Page 1110: ...RPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 40 1 08 33 Page 7 Code 01 AOM 145 1114 OR OR RED BEACON LIGHT PROTECTIVE LEN RED BEACON LIGHT PROTECTIVE LEN EM145AOM080025A DGN FIGURE 1...

Page 1111: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 33 Page 8 Code 01 REVISION 40 AOM 145 1114 FIGURE 17...

Page 1112: ...installed Sequence ITEM 3 Number required for dispatch Number 4 Remarks and or exceptions 49 AUXILIARY POWER UNIT 42 1 APU Starter Generator Air Intake Scoop Figure 18 1 0 May be missing provided APU...

Page 1113: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 49 Page 2 Code 01 REVISION 27 FIGURE 18...

Page 1114: ...Number installed Sequence ITEM 3 Number required for dispatch Number 4 Remarks and or exceptions 52 DOORS 10 1 Main Door Handgrip Figure 19 1 0 May be missing with no penalty 42 1 Service Door Handgri...

Page 1115: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 52 Page 2 Code 01 REVISION 27 FIGURE 19...

Page 1116: ...oor 414AB BB EB Figure 20 424AB BB EB Figure 21 6 4 A maximum of 1 per pylon for a total of 2 may be missing provided maximum airspeed is limited to 250 KIAS 0 65 M whichever is lower 50 2 Bleed Valve...

Page 1117: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 54 Page 2 Code 01 REVISION 27 FIGURE 20...

Page 1118: ...AIRPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 27 1 08 54 Page 3 Code 01 FIGURE 21...

Page 1119: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 54 Page 4 Code 01 REVISION 13 THIS PAGE IS LEFT INTENTIONALLY BLANK...

Page 1120: ...ator Trim Control Rod Fairing Figure 26 2 0 May be missing with no penalty 20 4 Elevator Access Door 335AB BB CB DB EB FB GB HB Figure 22 336AB BB CB DB EB FB GB HB Figure 23 16 15 One may be missing...

Page 1121: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 55 Page 2 Code 01 REVISION 27 FIGURE 22...

Page 1122: ...AIRPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 27 1 08 55 Page 3 Code 01 FIGURE 23...

Page 1123: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 55 Page 4 Code 01 REVISION 27 FIGURE 24...

Page 1124: ...AIRPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 27 1 08 55 Page 5 Code 01 FIGURE 25...

Page 1125: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 55 Page 6 Code 01 REVISION 27 FIGURE 26...

Page 1126: ...ssing with no penalty 30 2 Wing Tip Glareshield Figure 28 2 0 May be missing with no penalty 42 1 Wing Grounding Point Figure 29 2 0 One or both may be missing with no penalty provided a The hole is c...

Page 1127: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 57 Page 2 Code 01 REVISION 27 FIGURE 27...

Page 1128: ...AIRPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 27 1 08 57 Page 3 Code 01 FIGURE 28...

Page 1129: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 57 Page 4 Code 01 REVISION 27 FIGURE 29...

Page 1130: ...AIRPLANE OPERATIONS MANUAL CONFIGURATION DEVIATION LIST REVISION 27 1 08 57 Page 5 Code 01 FIGURE 30...

Page 1131: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 57 Page 6 Code 01 REVISION 27 FIGURE 31...

Page 1132: ...1 08 78 Page 1 Code 01 ATA CHAPTER 78 ENGINE EXHAUST System 1 2 Number installed Sequence ITEM 3 Number required for dispatch Number 4 Remarks and or exceptions 78 ENGINE EXHAUST 31 1 Plug Inhibition...

Page 1133: ...CONFIGURATION DEVIATION LIST AIRPLANE OPERATIONS MANUAL 1 08 78 Page 2 Code 01 REVISION 27 FIGURE 32...

Page 1134: ...SION 36 1 09 00 Page 1 Code 03 AOM 145 1114 SECTION 1 09 DISPATCH DEVIATIONS PROCEDURES MANUAL This section has been removed from your Airplane Operations Manual For Dispach Deviations Procedures refe...

Page 1135: ...DISPATCH DEVIATIONS PROCEDURES MANUAL AIRPLANE OPERATIONS MANUAL 1 09 00 Page 2 Code 03 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 1136: ...rgency Equipment Layout 1 10 06 Passenger Oxygen Masks Location 1 10 08 Passenger Floatable Seat and Life Jacket 1 10 10 Fire Extinguisher 1 10 15 Emergency Locator Transmitter ELT 1 10 20 Lighting 1...

Page 1137: ...ed emergency procedures Such procedures may be associated to contingencies not related to the airplane Emergency equipment includes those items used during in flight emergencies such as first aid kits...

Page 1138: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 36 1 10 05 Page 1 Code 01 AOM 145 1114 EMERGENCY EQUIPMENT EMERGENCY EQUIPMENT LOCATION TYPICAL COCKPIT AREA 1 OF 3...

Page 1139: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 05 Page 2 Code 01 REVISION 36 AOM 145 1114 COCKPIT AREA 2 OF 3...

Page 1140: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 36 1 10 05 Page 3 Code 01 AOM 145 1114 COCKPIT AREA 3 OF 3...

Page 1141: ...EM145AOM101004A DGN OXYGEN BOX DEPLOY TOOL WARDROBE OR GALLEY 1 MEGAPHONE OPTIONAL WARDROBE OR GALLEY FLASHLIGHT OVER ATTENDANT S SEAT PROTECTIVE BREATHING EQUIPMENT PBE 1 WARDROBE OR GALLEY LIFE VEST...

Page 1142: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 36 1 10 05 Page 5 Code 01 AOM 145 1114 FRONT PASSENGER AREA 2 OF 2...

Page 1143: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 05 Page 6 Code 01 REVISION 36 AOM 145 1114 REAR PASSENGER AREA 1 OF 2...

Page 1144: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 36 1 10 05 Page 7 Code 01 AOM 145 1114 REAR PASSENGER AREA 2 OF 2...

Page 1145: ...ight CHECK RED LIGHT First Aid Kit CONDITION Megaphone optional ON BOARD Water Extinguisher optional CONDITION Protective Breathing Equipment PBE SEALED Fire Extinguisher CONDITION Portable Oxygen Cyl...

Page 1146: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 01 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 1 50 SEATS...

Page 1147: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 01 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1148: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 02 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 2 50 SEATS...

Page 1149: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 02 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1150: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 03 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 3 50 SEATS...

Page 1151: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 03 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1152: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 04 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 3 50 SEATS...

Page 1153: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 04 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1154: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 05 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 4 49 SEATS...

Page 1155: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 05 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1156: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 06 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 4 49 SEATS...

Page 1157: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 06 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1158: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 07 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 5 48 SEATS...

Page 1159: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 07 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1160: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 08 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 5 48 SEATS...

Page 1161: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 08 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1162: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 09 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 6 50 SEATS...

Page 1163: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 09 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1164: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 12 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 4 49 SEATS...

Page 1165: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 12 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1166: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 29 2000 1 10 08 Page 1 Code 13 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 6 50 SEATS...

Page 1167: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 13 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1168: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION DECEMBER 20 2002 1 10 08 Page 1 Code 17 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 1 50 SEATS...

Page 1169: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 17 DECEMBER 20 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1170: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 30 1 10 08 Page 1 Code 20 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT CONFIGURATION FAB VIP 36 SEATS...

Page 1171: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 20 REVISION 30 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1172: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 33 1 10 08 Page 1 Code 21 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 6A 50 SEATS...

Page 1173: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 21 REVISION 33 INTENTIONALLY BLANK...

Page 1174: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 33 1 10 08 Page 1 Code 22 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 3 50 SEATS...

Page 1175: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 22 REVISION 33 INTENTIONALLY BLANK...

Page 1176: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 34 1 10 08 Page 1 Code 23 EMB 145 PASSENGER OXYGEN MASKS LOCATION INTERIOR ARRANGEMENT OPTION 2A 50 SEATS...

Page 1177: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 08 Page 2 Code 23 REVISION 34 INTENTIONALLY BLANK...

Page 1178: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 13 1 10 10 Page 1 Code 01 PASSENGER FLOATABLE SEAT AND LIFE JACKET PASSENGER FLOATABLE SEAT OPERATION...

Page 1179: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 10 Page 2 Code 01 REVISION 31 LIFE JACKET OPERATION...

Page 1180: ...or electronic equipment live electrical fire It is also allowed to be used on class A paper wood fabric rubber fires if the cabin configuration permits according to the fire extinguisher cabin configu...

Page 1181: ...1211 1301 2 5 lb B C CONFIGURATION 1 or 2 Halon 1211 2 5 lb B C 2 Halon 1211 1301 2 5 lb B C CONFIGURATION 2 and 1 water based 3 5 lb A 1 Halon 1211 1301 2 5 lb B C CONFIGURATION 3 and 1 Halon 1211 9...

Page 1182: ...ATIONS MANUAL EMERGENCY INFORMATION DECEMBER 20 2002 1 10 15 Page 3 Code 01 FIRE EXTINGUISHER OPERATION Precautions after fire extinguishing Look out for flashback Ventilate the compartment as promptl...

Page 1183: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 15 Page 4 Code 01 DECEMBER 20 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1184: ...vatory right ceiling panel an antenna located on the top rear and a remote panel located on the cockpit ELT may be manually or automatically activated In both cases a red light flashes on the cockpit...

Page 1185: ...ransmitting 2 ELT SWITCH guarded ON Activates the ELT ARM Allows the ELT to be automatically activated NOTE The TEST RESET function is provided by pressing ON waiting 1 second and then pressing ARM RE...

Page 1186: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION SEPTEMBER 20 1999 1 10 20 Page 3 Code 01 ELT 110 4 MODEL...

Page 1187: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 20 Page 4 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1188: ...the ELT front panel switch or remote switch in cockpit in both cases setting the switch to MAN position Automatic activation occurs when the ELT switch and the remote control switch are set to AUTO po...

Page 1189: ...unction the ELT alert light illuminates during 2 seconds If a failure is detected during the test the ELT alert light flashes For confirmation repeat the operation If the failure persists set the ELT...

Page 1190: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 34 1 10 20 Page 3 Code 02 ELT 96 AND 97 MODELS...

Page 1191: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 20 Page 4 Code 02 REVISION 13 INTENTIONALLY BLANK...

Page 1192: ...Country code ID code Position coordinates when connected to an ARTEX ELT NAV interface unit The system comprises a transmitter with an ON OFF switch and an impact switch installed in the lavatory rig...

Page 1193: ...smitting 2 ELT SWITCH GUARDED ON Activates the ELT ARM Allows the ELT to be automatically activated NOTE The TEST RESET function is provided by pressing ON waiting 1 second and then pressing ARM RESET...

Page 1194: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 31 1 10 20 Page 3 Code 03 ELT C406 2 MODEL...

Page 1195: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 20 Page 4 Code 03 REVISION 31 INTENTIONALLY BLANK...

Page 1196: ...MATION SEPTEMBER 20 1999 1 10 25 Page 1 Code 01 LIGHTING Refer to AOM VOLUME 2 Section 2 6 LIGHTING OXYGEN Refer to AOM VOLUME 2 Section 2 16 OXYGEN NAVIGATION AND COMMUNICATION Refer to AOM VOLUME 2...

Page 1197: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 25 Page 2 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1198: ...age 1 Code 01 LEAST RISK LOCATION The place inside airplane cabin where structural or system damages are the least likely to jeopardize flight safety is the third overhead bin from front of the cabin...

Page 1199: ...EMERGENCY INFORMATION AIRPLANE OPERATIONS MANUAL 1 10 30 Page 2 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1200: ...CY INFORMATION REVISION 30 1 10 35 Page 1 Code 01 EMERGENCY EXITS There are two forward doors main and service two overwing exits and two cockpit windows one each side that can be used for emergency e...

Page 1201: ...35 Page 2 Code 01 REVISION 30 EMERGENCY OVERWING EXITS Two emergency exit hatches exist for passenger evacuation in the event of an emergency They are located one on each side of the airplane centered...

Page 1202: ...AIRPLANE OPERATIONS MANUAL EMERGENCY INFORMATION REVISION 31 1 10 35 Page 3 Code 01 EMERGENCY EXIT OPERATION OUTSIDE CABIN...

Page 1203: ...r equipped with an equivalent modification factory incorporated the emergency exit hatches can be locked with locking pins On ground at pilot discretion the pins can be used but it must be removed and...

Page 1204: ...MANUAL EMERGENCY EVACUATION REVISION 26 1 11 00 Page 1 Code 01 SECTION 1 11 EMERGENCY EVACUATION TABLE OF CONTENTS Page Block Emergency Evacuation Procedure 1 11 05 Doors and Exits 1 11 40 Emergency R...

Page 1205: ...Y EVACUATION AIRPLANE OPERATIONS MANUAL 1 11 00 Page 2 Code 01 REVISION 13 INTRODUCTION This Section presents information which may be used at operators discretion to develop customized evacuation pro...

Page 1206: ...uel Shutoff Valve CLOSE APU and Engine Fire Extinguishing Bottles if necessary DISCHARGE Ventral Tank Transfer Knob if applicable OFF Electric Fuel Pumps OFF Electric Hydraulic Pumps OFF Cabin Crew NO...

Page 1207: ...EMERGENCY EVACUATION AIRPLANE OPERATIONS MANUAL 1 11 05 Page 2 Code 02 REVISION 13 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1208: ...CY EVACUATION REVISION 31 1 11 40 Page 1 Code 03 DOORS AND EXITS There are two forward doors main and service two overwing exits and two cockpit windows one each side that can be used for emergency ev...

Page 1209: ...RATIONS MANUAL 1 11 40 Page 2 Code 03 REVISION 29 MAIN DOOR Themaindoor airstairorjetwaytype islocatedattheforeleftsideofthefuselage AIRSTAIR MAIN DOOR OPERATION INSIDE CABIN NOTE Some airplanes may h...

Page 1210: ...AIRPLANE OPERATIONS MANUAL EMERGENCY EVACUATION REVISION 19 1 11 40 Page 3 Code 03 AIRSTAIR MAIN DOOR OPERATION OUTSIDE CABIN...

Page 1211: ...EMERGENCY EVACUATION AIRPLANE OPERATIONS MANUAL 1 11 40 Page 4 Code 03 REVISION 35 JETWAY MAIN DOOR OPERATION INSIDE CABIN...

Page 1212: ...AIRPLANE OPERATIONS MANUAL EMERGENCY EVACUATION REVISION 19 1 11 40 Page 5 Code 03 JETWAY MAIN DOOR OPERATION OUTSIDE CABIN...

Page 1213: ...RATIONS MANUAL 1 11 40 Page 6 Code 03 REVISION 29 SERVICE DOOR The service door provided at the right side of the forward passenger cabin is used for galley servicing and also as an emergency exit SER...

Page 1214: ...AIRPLANE OPERATIONS MANUAL EMERGENCY EVACUATION AUGUST 24 2001 1 11 40 Page 7 Code 03 SERVICE DOOR OPERATION OUTSIDE CABIN...

Page 1215: ...ode 03 SEPTEMBER 20 1999 EMERGENCY EXITS EMERGENCY OVERWING EXITS Two emergency exit hatches exist for passenger evacuation in the event of an emergency They are located one on each side of the aircra...

Page 1216: ...AIRPLANE OPERATIONS MANUAL EMERGENCY EVACUATION REVISION 31 1 11 40 Page 9 Code 03 EMERGENCY EXIT OPERATION OUTSIDE CABIN...

Page 1217: ...itate removal by moving the associated pilot seat backward NOTE Windows can not be opened from outside A rope is positioned above each window to assist evacuation COCKPIT DOOR Cockpit door located bet...

Page 1218: ...AIRPLANE OPERATIONS MANUAL EMERGENCY EVACUATION REVISION 30 1 11 40 Page 11 Code 03 COCKPIT WINDOW REMOVAL AND EVACUATION PROCEDURE...

Page 1219: ...EMERGENCY EVACUATION AIRPLANE OPERATIONS MANUAL 1 11 40 Page 12 Code 03 REVISION 25 SECURITY DOOR EMERGENCY EXIT PROCEDURE...

Page 1220: ...AIRPLANE OPERATIONS MANUAL EMERGENCY EVACUATION REVISION 30 1 11 40 Page 13 Code 03 STANDARD DOOR EMERGENCY EXIT PROCEDURE...

Page 1221: ...EMERGENCY EVACUATION AIRPLANE OPERATIONS MANUAL 1 11 40 Page 14 Code 03 REVISION 30 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1222: ...ION 18 1 11 45 Page 1 Code 01 EMERGENCY RESCUE CHARTS The Emergency Rescue Charts present emergency equipment location as well as emergency evacuation schematic These charts may be used at operators d...

Page 1223: ...EMERGENCY EVACUATION AIRPLANE OPERATIONS MANUAL 1 11 45 Page 2 Code 01 REVISION 33 EMERGENCY RESCUE CHART 1 OF 2...

Page 1224: ...AIRPLANE OPERATIONS MANUAL EMERGENCY EVACUATION REVISION 31 1 11 45 Page 3 Code 01 EMERGENCY RESCUE CHART 2 OF 2...

Page 1225: ...EMERGENCY EVACUATION AIRPLANE OPERATIONS MANUAL 1 11 45 Page 4 Code 01 REVISION 18 INTENTIONALLY BLANK...

Page 1226: ...NTENTS Page Block INTRODUCTION 1 12 00 EXTERNAL CONNECTIONS 1 12 05 TOWING 1 12 10 PARKING MOORING 1 12 15 COLD WEATHER OPERATION 1 12 20 FUEL SYSTEM SERVICING 1 12 25 ENGINE OIL SERVICING 1 12 30 APU...

Page 1227: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 00 Page 2 Code 01 REVISION 13 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1228: ...ed to the ground handling and servicing of the airplane They are intended to make flight crews familiar with the ordinary aspects of the subject as those tasks described herein normally are the respon...

Page 1229: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 00 Page 4 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1230: ...28 0 V 2 0 V 1 0 V DC when the GPU status is AVAILABLE The power source must be able to maintain the voltage within this range when the GPU status is IN USE Connecting a source out of these specifica...

Page 1231: ...PNEUMATIC START UNIT The pneumatic start unit is connected to the aircraft through the receptacle on the right side of the rear fuselage The output of the unit must be set between 40 and 45 psi This p...

Page 1232: ...127 mm H2O 5 in H2O maximum air temperature must not exceed 71 o C 160 o F and maximum flow must not exceed 3 6 m 3 min 127 ft 3 min 96 lbm min The source must be capable of supplying 50040 BTU h The...

Page 1233: ...UAL 1 12 05 Page 4 Code 01 SEPTEMBER 20 1999 STATIC GROUNDING There are three grounding points on the aircraft Two of them are installed on the lower surface of each wing leading edge and one is aft o...

Page 1234: ...1511 with plug specification MIL C 83413 4 and an alligator clip Examine the static ground cable for damage and to make sure that the end fittings are correctly attached CAUTION USE THE GROUNDING POIN...

Page 1235: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 05 Page 6 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1236: ...owing is permitted only for airplanes Post Mod SB 145 32 0065 or SB 145 32 0086 or SB 145 32 0102 or equipped with an equivalent modification factory incorporated Maximum nosewheel displacement during...

Page 1237: ...GTIPS AND TAIL CAN BE SEEN CLEARLY Close the main door except for airplanes equipped with wheeled main door If it is not necessary to tow the airplane with the hydraulic systems 1 and 2 pressurized De...

Page 1238: ...from system 1 to system 2 or vice versa always apply brakes with the pedals before pulling and releasing the emergency parking brake handle Set the emergency parking brake handle up Check if emergenc...

Page 1239: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 10 Page 4 Code 01 REVISION 39 AOM 145 1114 EM145AOM122017A DGN RAMP PANEL STEERING DISENGAGEMENT SWITCH COMPARTMENT...

Page 1240: ...llowing the steps below WARNING WHEN THE ENGINES AND APU ARE RUNNING DURING THE TOWING PROCEDURES MAKE SURE THAT ALL PERSONS ON THE GROUND STAY AWAY FROM HAZARDOUS AREAS Remove the lock pin from the g...

Page 1241: ...TOWING PROCEDURE REGARDLESS OF THE SPEED USING BRAKES CAN CAUSE DAMAGE TO THE AIRPLANE STRUCTURE AND OR TO THE NOSE LANDING GEAR ONLY WHEN THERE IS A RISK OF COLLISION OR DAMAGE TO THE AIRPLANE AND I...

Page 1242: ...ide pin from the towing point of the nose landing gear Remove the towbar assembly from the nose landing gear CAUTION CHECK WITH GROUND PERSONNEL IF THE NOSE WHEEL IS NEAR THE CENTER POSITION CLOSE TO...

Page 1243: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 10 Page 8 Code 01 REVISION 39 AOM 145 1114 EM145AOM121005A DGN TOWING POINT NOSE LANDING GEAR TOW BAR LOCK PIN GUIDE PIN TOWBAR TOWING EQUIPMENT...

Page 1244: ...brake Check if the brake ON light goes off NOTE Coordinate with ground personnel to release and apply the airplane emergency parking brake To prevent hydraulic fluid transference from system 1 to syst...

Page 1245: ...hydraulic fluid transference from system 1 to system 2 or vice versa always apply brakes with the pedals before pulling and releasing the emergency parking brake handle Make sure that nose wheel disp...

Page 1246: ...8 m 3 6 m 30 m 6 ft 7 in 26 ft 3 in 11 ft 10 in 14 ft 1 in 98 ft 5 in 22 ft 12 in 30 m 98 ft 5 in 10 8 m 3 6 m 26 ft 3 in 11 ft 10 in 3 m 9 ft 10 in 3 m 9 ft 10 in 2 m 6 ft 7 in 4 3 m 14 ft 1 in 6 m 1...

Page 1247: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 10 Page 12 Code 01 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 1248: ...ds higher than 50 knots for the mechanical gust lock system or above 65 knots for the electromechanical gust lock system If the airplane is exposed to wind gusts with the gust lock in the unlocked FRE...

Page 1249: ...Install the covers to the pitot tubes total air temperature TAT sensor tail cone nose cowl ice detector engine APU air intakes and exhaust nozzles and anemometrical static ports RETURN TO SERVICE Remo...

Page 1250: ...28 2000 1 12 15 Page 3 Code 01 MOORING Mooring is necessary when the weather conditions are bad or unknown The area where the aircraft is to be parked in and moored must be paved and level with groun...

Page 1251: ...rete 60 Kt To moor the aircraft proceed as follows Tow the aircraft to a parking area where there are tiedown anchors available Carry out the normal parking procedure Install the tiedown rings two one...

Page 1252: ...ng gear wheels For an icy ramp leave Emergency Parking Brakes applied Otherwise Emergency Parking Brakes must not be applied to avoid freezing of the brakes Install protective covers on engines and AP...

Page 1253: ...es with the water thereby causing the mixture to become less effective or to run off Ice can begin to form again after enough dilution has occurred and freezing point begins to rise Deicing anti icing...

Page 1254: ...hanced performance fluid and offers significant operational advantages in terms of holdover times However thickened fluids may dry out during flight and residues may accumulate in aerodynamically quie...

Page 1255: ...ted If contamination is suspected the airplane should be returned for additional deicing or anti icing For practical results the holdover time must be equal to or greater than the estimated time from...

Page 1256: ...e performed so that the residues accumulation in the critical areas is minimized The use of hot water or heated mix of type I fluid water for the first step of a two step deicing anti icing process ma...

Page 1257: ...mage FOD ingestion The best spray is straight in relation to the airplane centerline in the aft direction see figure This is applicable when spraying either over or under the stabilizer surface Straig...

Page 1258: ...AIRPLANE OPERATIONS MANUAL GROUND SERVICING REVISION 37 1 12 20 Page 7 Code 01 AOM 145 1114 STRAIGHT APPLICATION IN RELATION TO AIRPLANE CENTERLINE 45 FLUID APPLICATION...

Page 1259: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 20 Page 8 Code 01 REVISION 37 AOM 145 1114 BACK SPRAYING CROSS SPRAYING APPLICATION...

Page 1260: ...centerline of the fuselage and then outboard letting the fluid cascade down and across the windows Fluid must not be sprayed directly onto windows and window seals doors and doors seals air conditioni...

Page 1261: ...ozen contamination on airplane surfaces the anti icing operation requires that fluids be distributed uniformly over surfaces In order to control uniformity all horizontal surfaces must be visually che...

Page 1262: ...LUIDS Only Deicing Anti icing fluids certified under specifications below are approved to be used in the EMB 145 airplane models Deicing Anti icing Fluid Specification Type I SAE AMS 1424 Types II III...

Page 1263: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 20 Page 12 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 1264: ...ator shows zero select the desired fuel quantity for the airplane Remove the protection cover from the pressure refueling adapter Connect the refueling nozzle to the pressure refueling adapter Pressur...

Page 1265: ...system FUEL QUALITY CONTROL Before accepting delivery from the fuel supplier a check should be made with the purpose of ensuring that fuel intended for use in airplane is in a fit state for use Fuel s...

Page 1266: ...the LOW 2 position When the selected fuel quantity is reached set the defueling switch to the CLOSED position and make sure its light is extinguished CAUTION DO NOT PERMIT THE FUEL PUMPS TO RUN DRY D...

Page 1267: ...A DGN DEFUELING DEVICE SHUTOFF VALVE DEFUELING CART DEFUELING PORT CAP GRAVITY DEFUELING EQUIPMENT Gravity defueling is accomplished by installing the defueling valve to the defueling port and putting...

Page 1268: ...drained periodically to remove free water and contaminants from the tank bottom on intervals no longer than 100 FH or 7 calendar days whichever occurs first To drain place a flask below the draining...

Page 1269: ...tween 2163 and 2791 liters 571 and 737 US gal the external measuring stick provides a correct fuel level indication Above 2791 liters 737 US gal it is not possible to measure the fuel level through th...

Page 1270: ...e 04 AOM 145 1114 STICK POSITION AIRPLANES WITHOUT WING STUB TANK AIRPLANES WITH WING STUB TANK LITERS US GAL LITERS US GAL Wing Stub Min 7 2 Tank Max 783 207 Internal Min 448 118 781 206 Point Max 15...

Page 1271: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 25 Page 8 Code 04 REVISION 38 AOM 145 1114 EM145AOM082011A DGN STICK MEASURING MEASURING POINTS MEASURING STICK POINTS AIRPLANES WITHOUT WING STUB TANK...

Page 1272: ...AIRPLANE OPERATIONS MANUAL GROUND SERVICING REVISION 38 1 12 25 Page 9 Code 04 AOM 145 1114 MEASURING POINTS MEASURING STICK EM145AOM082029A DGN MEASURING STICK POINTS AIRPLANES WITH WING STUB TANK...

Page 1273: ...1583 418 0 8 497 131 1597 422 0 9 505 133 1610 425 1 0 512 135 1623 429 1 1 520 137 1637 432 1 2 527 139 1645 435 1 3 535 141 1663 439 1 4 543 143 1677 443 1 5 550 145 1690 447 1 6 558 148 1703 450 1...

Page 1274: ...03 186 1931 510 3 4 712 188 1944 514 3 5 721 191 1957 517 3 6 730 193 1971 521 3 7 740 195 1984 524 3 8 749 198 1998 528 3 9 759 200 2011 531 4 0 768 203 2024 535 4 1 778 205 2037 538 4 2 787 208 2051...

Page 1275: ...5 8 952 252 5 9 963 254 6 0 974 257 6 1 985 260 6 2 996 263 6 3 1007 266 6 4 1018 269 6 5 1030 272 6 6 1041 275 6 7 1052 278 6 8 1064 281 6 9 1076 284 7 0 1087 287 7 1 1099 290 7 2 1111 293 7 3 1123 2...

Page 1276: ...1258 332 8 5 1270 336 8 6 1283 339 8 7 1296 342 8 8 1309 346 8 9 1322 349 9 0 1335 353 9 1 1348 356 9 2 1361 360 9 3 1374 363 9 4 1388 367 9 5 1401 370 9 6 1415 374 9 7 1428 377 9 8 1442 381 9 9 1455...

Page 1277: ...601 56 15 0 9 868 229 2288 605 63 17 1 0 878 232 2301 608 69 18 1 1 888 235 2314 611 74 20 1 2 898 237 2327 615 80 21 1 3 907 240 2340 618 85 23 1 4 917 242 2354 622 90 24 1 5 927 245 2368 626 95 25 1...

Page 1278: ...91 188 50 3 3 1130 299 2625 693 195 51 3 4 1143 302 2634 696 201 53 3 5 1156 305 2643 698 207 55 3 6 1169 309 2651 700 213 56 3 7 1182 312 2658 702 218 58 3 8 1194 316 2666 704 224 59 3 9 1208 319 267...

Page 1279: ...374 320 85 5 6 1431 378 327 86 5 7 1444 381 334 88 5 8 1457 385 342 90 5 9 1470 388 350 92 6 0 1483 392 357 94 6 1 1496 395 365 97 6 2 1509 399 374 99 6 3 1522 402 382 101 6 4 1535 405 390 103 6 5 15...

Page 1280: ...558 147 8 4 1822 481 567 150 8 5 1838 486 576 152 8 6 1855 490 585 154 8 7 1872 494 593 157 8 8 1889 499 602 159 8 9 1906 503 611 161 9 0 1923 508 620 164 9 1 1941 513 629 166 9 2 1958 517 639 169 9...

Page 1281: ...g with One Engine Running procedure ahead The airplane must be parked in an area designated by the Airport Authority with free access to fire fighting equipment and personnel Keep the main door open a...

Page 1282: ...pilot is responsible for informing all the flight and ground crew that the airplane is being refueled with passengers on board or embarking disembarking Engines must be off Crew staff and passengers...

Page 1283: ...itial start or a restart after a normal shutdown APU shutdown is allowed during the refueling operations If the APU fails to start during refueling Complete refueling prior to another start attempt Do...

Page 1284: ...te there is no mandatory action Engine oil consumption rates can increase as engine hours cycles increase To fill the tank with oil proceed as follows Remove the filler cap from the engine oil tank Th...

Page 1285: ...ARBON DEPOSITS LEFT BY THOSE OILS THIS CLEANING PROCESS CAN LEAD TO OIL SYSTEM PROBLEMS SUCH AS BLOCKED PASSAGEWAYS AND SCREENS CHANGING FROM BPTO 2380 MIL JET II OR AEROSHELL ROYCO 500 TO MOBIL JET 2...

Page 1286: ...AIRPLANE OPERATIONS MANUAL GROUND SERVICING REVISION 37 1 12 30 Page 3 Code 01 AOM 145 1114 ENGINE OIL FILLING AND OIL LEVEL CHECK...

Page 1287: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 30 Page 4 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 1288: ...l Castrol 5050 Castrol Calstex Sato 5S Local supplier BPTO 2197 BPTO 2380 Air BP Lubricants Hatcol 3211 Local supplier Mobil Jet Oil II Mobil Mobil Jet Oil 254 Mobil Aeroshell Royco Turbine Oil 500 Ro...

Page 1289: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 35 Page 2 Code 01 REVISION 37 AOM 145 1114 APU OIL FILLING AND OIL LEVEL CHECK...

Page 1290: ...ir until you have the correct full level mark Low oil level in the reservoir can be a sign that there is a leak in the system After servicing the hydraulic system close the related hydraulic fluid res...

Page 1291: ...BSORBER PRESSURE The main and nose landing gear shock absorber sometimes need nitrogen to be filled Nitrogen is filled through a charging valve installed at the landing gear Filling pressure is a func...

Page 1292: ...AIRPLANE OPERATIONS MANUAL GROUND SERVICING DECEMBER 20 2002 1 12 40 Page 3 Code 01 NOSE LANDING GEAR SERVICING...

Page 1293: ...5 5 0 EMB 145 EU 82 4 0 145 5 0 EMB 145 EP 82 4 0 148 5 0 EMB 145 MP MK 84 2 2 150 3 3 EMB 145 LR LU 84 2 2 160 4 4 EMB 135 ER 84 2 2 134 3 3 EMB 135 LR 84 2 2 148 3 3 ERJ 140 ER EMB 135 KE 84 2 2 145...

Page 1294: ...pistons 2 of the brake assembly for operation Brake wear indicator positions must be inspected with brake pressurized brake applied Inspect the brake wear indicators for visible cracks Inspect the bra...

Page 1295: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 40 Page 6 Code 01 DECEMBER 20 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1296: ...made up of pilot copilot and observer 1500 psi Portable oxygen cylinders are distributed along the cabin for passenger and flight attendant emergencies For airplane dispatchability the minimum pressur...

Page 1297: ...12 45 Page 2 Code 01 REVISION 38 AOM 145 1114 EM145AOM121016A DGN PRESSURE GAUGE OXYGEN CYLINDER SHUTOFF VALVE REF CHARGING VALVE OXYGEN CHARGER ADAPTER PROTECTIVE CAP ACCESS DOOR 124AR OXYGEN SOURCE...

Page 1298: ...ain installed on the servicing panel near its control handle To drain the water tank remove the cap and pull the handle Draining is recommended when freezing or icing conditions are forecast after the...

Page 1299: ...12 50 Page 2 Code 01 REVISION 13 TOILET SERVICING Toilet waste disposal servicing is accomplished by accessing a panel at the rear right side of the fuselage A sanitary service unit must be connected...

Page 1300: ...lock the drain control handle to open the holding tank drain valve Continue the tank drainage until the waste flow stops Flush with water through the rinse nipple for approximately 3 minutes Release t...

Page 1301: ...GROUND SERVICING AIRPLANE OPERATIONS MANUAL 1 12 50 Page 4 Code 01 SEPTEMBER 20 1999 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1302: ...sage or fault is presented before starting to follow this chapter after dispatch These procedures may vary for different airports This chapter is organized in a four column table as follows ATA column...

Page 1303: ...uisance EICAS message or fault is not cleared maintenance personnel must be notified to clear the condition Effectivity and Fault Condition must be observed Ground Resets Procedures should be accompli...

Page 1304: ...ted Navigation Unit 1 ADF 1 Set the cursor of RMU 1 to the ADF 1 window 2 Do the test of the frequency selection a Put the cursor on the selected frequency code b Turn the dual concentric knobs A freq...

Page 1305: ...ated Navigation Unit 2 ADF 1 Set the cursor of RMU 2 to the ADF 2 window 2 Do the test of the frequency selection a Put the cursor on the selected frequency code b Turn the dual concentric knobs A fre...

Page 1306: ...nit 1 DME 1 On RMU 1 push the DME function key 2 Move the cursor of RMU 1 to the DME 1 window 3 Do the test of frequency selection a Put the cursor on the selected frequency code b Turn the dual conce...

Page 1307: ...nit 2 DME 1 On RMU 2 push the DME function key 2 Move the cursor of RMU 2 to the DME 2 window 3 Do the test of frequency selection a Put the cursor on the selected frequency code b Turn the dual conce...

Page 1308: ...witch and ESSENTIAL POWER pushbutton pushbutton released on the electrical panel on the overhead panel are set at the AUTO position 4 Check that GPU pushbutton on the electrical panel on the overhead...

Page 1309: ...seconds The roll trim system is automatically deactivated in 3 seconds 2 Push the roll trim switch to the RWD position for approximately 3 seconds The roll trim system is automatically deactivated in...

Page 1310: ...e maintained stationary during the ISIS initialization 2 The display shows an initialization page for 70 seconds ISIS SMITHS or for 90 seconds ISIS THALES 3 Wait until the ISIS completes its initializ...

Page 1311: ...Directional Trim Locked Rudder trim switch has to be pressed 3 times before the surface responds and the system operates at the fourth try Transitory condition of yaw trim electrical circuit Rudder T...

Page 1312: ...he operational check of the yaw trim Move the YAW TRIM switch to the LEFT position On the EICAS display the arrow of the YAW TRIM indication moves to the left NOTE The system cycle is limited in 3 sec...

Page 1313: ...nel FCU Do the electrical fuel quantity indication check On the repeater indicator panel set the toggle switch to the TEST position and clear the fault message If passes the electrical fuel quantity i...

Page 1314: ...than 60 knots The airplane must be maintained stationary during the ISIS initialization 2 The display shows an initialization page for 90 seconds 3 Wait until the ISIS completes its initialization 34...

Page 1315: ...ND toggle switch on the maintenance panel 1 The EICAS display shows these messages and indications FUEL 1 2 LO LEVEL WARNING TANK 1 2 shows 1130 kg 10 kg 2500 lb 2 The MFD shows these indications TANK...

Page 1316: ...than 60 knots The airplane must be maintained stationary during the ISIS initialization 2 The display shows an initialization page for 90 seconds 3 Wait until the ISIS completes its initialization 34...

Page 1317: ...the Yaw trim a Move the YAW TRIM switch to the LEFT position On the EICAS display the arrow of the YAW TRIM indication moves to the left NOTE The system cycle time is limited in 3 seconds after this t...

Page 1318: ...S 1 On the circuit breaker panel open and close the INTEG STBY circuit breaker NOTE Before turning on the ISIS make sure that there is no dynamic pressure applied to Pitot Static 3 It must be equivale...

Page 1319: ...AHRS 1 ATT MODE EICAS 1 After the airplane is brought to a stop at the ramp or hangar power off the AHRS 1 Open the circuit breaker AHRS 1 2 Reapply power and try to align the AHRS in a normal fashio...

Page 1320: ...mode key and the NEXT function key NAV INDEX 2 2 page comes into view Push the POS INIT 3L left line select key POS INIT 1 1 page comes into view Push the LOAD 2R right line select key to update the F...

Page 1321: ...900 computer For airplanes with single or dual Universal FMS NOTE Operator can use either the FMS CDU or the bezel pushbuttons of the pilot s MFD to enter the present position a FMS CDU On the FMS CD...

Page 1322: ...e AH 900 computer NOTE At the end of the alignment the AHRU conducts an alignment performance test on the entered latitude If the entered does not pass the alignment performance test the AHRS 1 ALN FA...

Page 1323: ...ode key and the NEXT function key NAV INDEX 2 2 page comes into view Push the POS INIT 3L left line select key POS INIT 1 1 page comes into view Push the LOAD 2R right line select key to update the FM...

Page 1324: ...900 computer For airplanes with single or dual Universal FMS NOTE Operator can use either the FMS CDU or the bezel pushbuttons of the pilot s MFD to enter the present position a FMS CDU On the FMS CDU...

Page 1325: ...e AH 900 computer NOTE At the end of the alignment the AHRU conducts an alignment performance test on the entered latitude If the entered does not pass the alignment performance test the AHRS 1 ALN FA...

Page 1326: ...ircuit breaker panel 3 Press both brake pedals and verify that the message remains extinguished 31 CHECK IC 2 SW EICAS On the circuit breaker panel open the IC 2 circuit breaker and close it after a f...

Page 1327: ...e SG pushbutton on the pilot Reversionary Panel Is the SG pushbutton pressed when the DAU 1B FAIL message appears YES Open and then close the IC 2 circuit breaker on the overhead circuit breakers pane...

Page 1328: ...ushbutton on the pilot Reversionary Panel Is the SG pushbutton pressed when the DAU 2B FAIL message appears YES Open and then close the IC 2 circuit breaker on the overhead circuit breakers panel 31 D...

Page 1329: ...appears YES Open and then close the IC 2 circuit breaker on the overhead circuit breakers panel 34 DU 1 FAN FAIL EICAS On the circuit breaker panel open and close PFD 1 circuit breaker D13 34 DU 2 FA...

Page 1330: ...pears If yes on the pilot reversionary panel rotate the MFD switch to the normal position The EICAS screen shows on the EICAS display DU 3 34 DU 4 OVHT EICAS Check if the DU 4 OVHT message appears for...

Page 1331: ...position NOTE The airplane must be maintained stationary during the IRS 1 alignment 3 Wait until the alignment is complete In case of IRS 1 FAIL message does not disappear a Set the MSU 1 rotary swit...

Page 1332: ...d CDU 1 CDU 2 FMC 1 FMC 2 GPS 1 and GPS 2 i Set the MSU 1 rotary switch to ALIGN j Enter the correct present position NOTE The airplane must be kept stationary during the IRS 1 alignment k Wait until...

Page 1333: ...2 FMC 1 FMC 2 GPS 1 and GPS 2 e Wait at least 3 seconds f On the overhead electrical panel push the BACKUP pushbutton again the stripped bar extinguishes g On the overhead circuit breaker panel close...

Page 1334: ...chapter after dispatch These procedures may vary for different airports This chapter is organized in a four column table as follows ATA column gives the ATA number for the related message or fault ME...

Page 1335: ...essage or fault is not cleared if applicable the maintenance personnel must be notified to clear the condition Effectivity and Fault Condition must be observed Ground Resets Procedures should be accom...

Page 1336: ...e cursor on the selected frequency code b Turn the dual concentric knobs A frequency code can be set 3 Do the self test a Set the RMU 1 to the ADF 1 window b Push and hold the RMU TST function key On...

Page 1337: ...he cursor on the selected frequency code b Turn the dual concentric knobs A frequency code can be set 3 Do the self test a Set the RMU to the ADF 1 window b Push and hold the RMU TST function key On t...

Page 1338: ...e b Turn the dual concentric knobs A frequency code can be set 4 Do the self test a Set the RMU 1 to the DME 1 window b Push and hold the RMU TST function key On the RMU the DME 1 window shows TEST an...

Page 1339: ...e b Turn the dual concentric knobs A frequency code can be set 4 Do the self test a Set the RMU 1 to the DME 1 window b Push and hold the RMU TST function key On the RMU the DME 1 window shows TEST an...

Page 1340: ...e fault occurred during the airplane power up NOTE The CMU takes approximately 1 minute or 2 minutes to restart During this time the CDU displays ACARS DMU FAILED 27 Aileron No roll control through th...

Page 1341: ...ed stationary during the ISIS initialization 2 The display shows an initialization page for 70 seconds ISIS SMITHS or for 90 seconds ISIS THALES 3 Wait until the ISIS completes its initialization 34 A...

Page 1342: ...hase In flight the pilot must maintain the airplane in straight and level flight and at constant speed before pushing the CAGE button during this phase 2 Make sure that the attitude function has been...

Page 1343: ...switch to the LEFT position On the EICAS display the arrow of the YAW TRIM indication moves to the left NOTE The system cycle is limited in 3 seconds after this time you must to release the switch and...

Page 1344: ...itch to the LEFT position On the EICAS display the arrow of the YAW TRIM indication moves to the left NOTE The system cycle is limited in 3 seconds after this time you must to release the switch and m...

Page 1345: ...Do the electrical fuel quantity indication check Transitory condition of the wing fuel conditioning unit On the repeater indicator panel set the toggle switch to the TEST position and clear the fault...

Page 1346: ...0 knots The airplane must be maintained stationary during the ISIS initialization 2 The display shows an initialization page for 90 seconds 3 Wait until the ISIS completes its initialization 34 MAINT...

Page 1347: ...the MFD Move the FUEL QTY IND toggle switch on the maintenance panel 1 The EICAS display shows these messages and indications FUEL 1 2 LO LEVEL WARNING TANK 1 2 shows 1130 kg 10 kg 2500 lb 2 The MFD...

Page 1348: ...60 knots The airplane must be maintained stationary during the ISIS initialization 2 The display shows an initialization page for 90 seconds 3 Wait until the ISIS completes its initialization 34 SSEC...

Page 1349: ...TRIM switch to the LEFT position On the EICAS display the arrow of the YAW TRIM indication moves to the left NOTE The system cycle time is limited in 3 seconds after this time you must to release the...

Page 1350: ...ker NOTE Before turning on the ISIS make sure that there is no dynamic pressure applied to Pitot Static 3 It must be equivalent to an airspeed equal to or greater than 60 knots The airplane must be ma...

Page 1351: ...TT MODE EICAS 1 After the airplane is brought to a stop at the ramp or hangar power off the AHRS 1 Open the circuit breaker AHRS 1 C2 2 Reapply power and try to align the AHRS in a normal fashion 34 A...

Page 1352: ...ey and the NEXT function key NAV INDEX 2 2 page comes into view Push the POS INIT 3L left line select key POS INIT 1 1 page comes into view Push the LOAD 2R right line select key to update the FMS pos...

Page 1353: ...omputer For airplanes with single or dual Universal FMS NOTE Operator can use either the FMS CDU or the bezel pushbuttons of the pilot s MFD to enter the present position a FMS CDU On the FMS CDU on t...

Page 1354: ...00 computer NOTE At the end of the alignment the AHRU conducts an alignment performance test on the entered latitude If the entered does not pass the alignment performance test the AHRS 1 ALN FAULT me...

Page 1355: ...y and the NEXT function key NAV INDEX 2 2 page comes into view Push the POS INIT 3L left line select key POS INIT 1 1 page comes into view Push the LOAD 2R right line select key to update the FMS posi...

Page 1356: ...mputer For airplanes with single or dual Universal FMS NOTE Operator can use either the FMS CDU or the bezel pushbuttons of the pilot s MFD to enter the present position a FMS CDU On the FMS CDU on th...

Page 1357: ...00 computer NOTE At the end of the alignment the AHRU conducts an alignment performance test on the entered latitude If the entered does not pass the alignment performance test the AHRS 1 ALN FAULT me...

Page 1358: ...a few seconds 31 DAU 1A FAIL EICAS Check the SG pushbutton on the pilot Reversionary Panel Is the SG pushbutton pressed when the DAU 1A FAIL message appears YES Open and then close the IC 2 circuit br...

Page 1359: ...cuit breakers panel and the IC 1 circuit breaker on the backup relay box Close the IC 1 circuit breaker on the overhead circuit breakers panel and the IC 1 circuit breaker on the backup relay box 31 D...

Page 1360: ...reakers panel and the IC 1 circuit breaker on the backup relay box Close the IC 1 circuit breaker on the overhead circuit breakers panel and the IC 1 circuit breaker on the backup relay box 31 DAU 1 W...

Page 1361: ...n the backup relay box Close the IC 1 circuit breaker on the overhead circuit breakers panel and the IC 1 circuit breaker on the backup relay box 34 DU 1 FAN FAIL EICAS On the circuit breaker panel op...

Page 1362: ...If yes on the pilot reversionary panel rotate the MFD switch to the normal position The EICAS screen shows on the EICAS display DU 3 34 DU 4 OVHT EICAS Check if the DU 4 OVHT message appears for appro...

Page 1363: ...ion NOTE The airplane must be maintained stationary during the IRS 1 alignment 3 Wait until the alignment is complete In case of IRS 1 FAIL message does not disappear a Set the MSU 1 rotary switch to...

Page 1364: ...1 CDU 2 FMC 1 FMC 2 GPS 1 and GPS 2 i Set the MSU 1 rotary switch to ALIGN j Enter the correct present position NOTE The airplane must be kept stationary during the IRS 1 alignment k Wait until the al...

Page 1365: ...1 FMC 2 GPS 1 and GPS 2 e Wait at least 3 seconds f On the overhead electrical panel push the BACKUP pushbutton again the stripped bar extinguishes g On the overhead circuit breaker panel close IRS 2...

Page 1366: ...ect to U S Export Administration Regulation EAR and other countries export control laws and regulations Diversion contrary to the EAR and other laws and regulations is strictly forbidden The above res...

Page 1367: ......

Page 1368: ...structive suggestions on how we can further improve our documentation or service Your feedback will be acknowledged and we will advise you of the action we intend to take Sincerely Embraer Flight Oper...

Page 1369: ...ge Code Date of Page Revision Name Position Company Fax Number Phone Number E Mail Comment Suggestion Space reserved for Embraer CCF n Comment received Date Acknowledged Person in Charge Action to be...

Page 1370: ...N 12 JUN 01 1999 REVISION 13 SEP 20 1999 REVISION 14 DEC 15 1999 REVISION 15 APR 28 2000 REVISION 16 SEP 29 2000 REVISION 17 MAR 30 2001 REVISION 18 JUN 29 2001 REVISION 19 AUG 24 2001 REVISION 20 OCT...

Page 1371: ...Page 2 Code 105 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 REVISION 40 NOV 14 2013 REVISION 41 MAR 06 2015 NOTE The references to the deleted pages from the previous rev...

Page 1372: ...ON 41 2 LEP 7 105 REVISION 41 2 LEP 8 105 REVISION 41 2 LEP 9 105 REVISION 41 2 LEP 10 105 REVISION 41 2 LEP 11 105 REVISION 41 2 LEP 12 105 REVISION 41 2 LEP 13 105 REVISION 41 2 LEP 14 105 REVISION...

Page 1373: ...41 2 LEP 42 105 REVISION 41 2 TOC 1 01 JUN 28 2002 ALL 2 TOC 2 01 JUN 28 2002 2 01 00 1 01 SEP 29 2000 ALL 2 01 00 2 01 DEC 20 2002 2 01 00 3 01 DEC 20 2002 2 01 00 4 01 JUN 28 2002 2 01 00 4A 01 DEC...

Page 1374: ...1 01 OCT 02 2001 Attendant s panel 2 02 15 2 01 OCT 02 2001 2 02 15 3 01 OCT 02 2001 2 02 15 4 01 OCT 02 2001 2 02 15 5 01 OCT 02 2001 2 02 15 6 01 OCT 02 2001 2 02 15 7 01 OCT 02 2001 2 02 15 8 01 O...

Page 1375: ...REVISION 20 2 02 35 4 02 REVISION 26 2 02 35 5 02 REVISION 26 2 02 35 6 02 REVISION 26 2 02 40 1 01 REVISION 37 Access doors and hatches 2 02 40 2 01 REVISION 37 2 02 40 3 01 REVISION 37 2 02 40 4 01...

Page 1376: ...REVISION 25 2 02 65 1 01 REVISION 25 Cockpit Security Door 2 02 65 2 01 REVISION 27 2 02 65 3 01 REVISION 25 2 02 65 4 01 REVISION 25 2 02 65 5 01 REVISION 25 2 02 65 6 01 REVISION 25 2 02 70 1 01 REV...

Page 1377: ...20 2002 2 04 05 19 01 JUN 28 2002 2 04 05 20 01 JUN 28 2002 2 04 05 21 01 JUN 28 2002 2 04 05 22 01 DEC 20 2002 2 04 05 23 01 JUN 28 2002 2 04 05 24 01 JUN 28 2002 2 04 05 25 01 JUN 28 2002 2 04 05 2...

Page 1378: ...01 JUN 28 2002 2 04 10 17 01 JUN 28 2002 2 04 10 18 01 JUN 28 2002 2 04 13 1 01 REVISION 39 ALL 2 04 13 2 01 REVISION 39 2 04 13 3 01 REVISION 39 2 04 13 4 01 REVISION 39 2 04 13 5 01 REVISION 39 2 0...

Page 1379: ...23 2 04 25 1 01 REVISION 39 ALL 2 04 25 2 01 REVISION 39 2 04 25 3 01 REVISION 39 2 04 25 4 01 REVISION 39 2 04 25 5 01 REVISION 39 2 04 25 6 01 REVISION 39 2 04 25 7 01 REVISION 39 2 04 25 8 01 REVI...

Page 1380: ...01 REVISION 38 2 04 30 27 01 REVISION 38 2 04 30 28 01 REVISION 38 2 04 30 29 01 REVISION 38 2 04 30 30 01 REVISION 38 2 04 30 31 01 REVISION 38 2 04 30 32 01 REVISION 38 2 04 30 33 01 REVISION 38 2 0...

Page 1381: ...EVISION 36 2 04 40 3 01 REVISION 37 2 04 40 4 01 REVISION 38 2 04 40 5 01 REVISION 36 2 04 40 6 01 REVISION 36 2 04 40 7 01 REVISION 36 2 04 40 8 01 REVISION 40 2 04 40 9 01 REVISION 38 2 04 40 10 01...

Page 1382: ...01 REVISION 36 2 05 10 1 01 REVISION 22 ALL 2 05 10 2 01 REVISION 29 2 05 10 3 01 MAR 28 2002 2 05 10 4 01 MAR 28 2002 2 05 10 5 01 REVISION 22 2 05 10 6 01 REVISION 26 2 05 10 6A 01 JUN 28 2002 2 05...

Page 1383: ...2 05 15 3 01 MAR 28 2002 2 05 15 4 01 MAR 28 2002 2 05 15 5 01 MAR 28 2002 2 05 15 6 01 MAR 28 2002 2 05 15 7 01 REVISION 29 2 05 15 8 01 REVISION 22 2 05 20 1 01 REVISION 41 ALL 2 05 20 2 01 REVISIO...

Page 1384: ...JAN 21 2002 2 06 15 6 01 JAN 21 2002 2 06 15 7 01 JAN 21 2002 2 06 15 8 01 JAN 21 2002 2 06 20 1 01 REVISION 24 Emergency lighting 2 06 20 2 01 REVISION 25 2 06 20 3 01 JAN 21 2002 2 06 20 4 01 JAN 2...

Page 1385: ...ISION 39 Baggage compart protection 2 07 20 2 01 REVISION 36 2 07 20 3 01 REVISION 36 2 07 20 4 01 REVISION 36 2 07 20 5 01 REVISION 36 2 07 20 6 01 REVISION 36 2 07 20 7 01 REVISION 36 2 07 20 8 01 R...

Page 1386: ...2 09 00 1 01 JAN 21 2002 ALL 2 09 00 2 01 JAN 21 2002 2 09 05 1 01 REVISION 37 General 2 09 05 2 01 REVISION 37 2 09 05 3 01 REVISION 37 2 09 05 4 01 REVISION 37 2 09 05 5 01 REVISION 37 2 09 05 6 01...

Page 1387: ...L 2 10 25 2 01 JUN 28 2002 2 10 30 1 01 REVISION 37 ALL 2 10 30 2 01 REVISION 37 2 10 30 3 01 REVISION 37 2 10 30 4 01 REVISION 37 2 10 30 5 01 REVISION 37 2 10 30 6 01 REVISION 37 2 10 35 1 01 REVISI...

Page 1388: ...REVISION 41 2 10 50 18 01 REVISION 41 2 10 50 19 01 REVISION 41 2 10 50 20 01 REVISION 41 2 10 50 21 01 REVISION 41 2 10 50 22 01 REVISION 41 2 10 60 1 01 REVISION 39 ALL 2 10 60 2 01 REVISION 39 2 1...

Page 1389: ...except China Eastern 2 12 00 2 01 REVISION 38 2 12 05 1 01 REVISION 38 ALL 2 12 05 2 01 REVISION 38 2 12 05 3 01 REVISION 38 2 12 05 4 01 REVISION 38 2 12 05 5 01 REVISION 38 2 12 05 6 01 REVISION 38...

Page 1390: ...ION 40 2 12 15 6 01 REVISION 40 2 12 15 7 01 REVISION 40 2 12 15 8 01 REVISION 40 2 12 15 9 01 REVISION 40 2 12 15 10 01 REVISION 40 2 12 15 11 01 REVISION 40 2 12 15 12 01 REVISION 40 2 13 00 1 01 RE...

Page 1391: ...01 JUN 29 2001 2 13 15 4 01 JUN 29 2001 2 13 15 5 01 JUN 29 2001 2 13 15 6 01 JUN 28 2002 2 13 15 7 01 JUN 29 2001 2 13 15 8 01 JUN 29 2001 2 13 15 9 01 AUG 24 2001 2 13 15 10 01 JUN 29 2001 2 13 20 1...

Page 1392: ...VISION 18 ALL 2 13 35 2 01 REVISION 27 2 13 35 3 01 REVISION 18 2 13 35 4 01 REVISION 30 2 13 35 5 01 JUN 29 2001 2 13 35 6 01 AUG 24 2001 2 14 00 1 01 REVISION 29 ALL except XR 2 14 00 2 01 REVISION...

Page 1393: ...2 14 10 17 01 REVISION 38 2 14 10 18 01 REVISION 38 2 14 15 1 01 JAN 21 2002 ALL except High Alt 2 14 15 2 01 JUN 29 2001 2 14 15 3 01 REVISION 19 2 14 15 4 01 REVISION 29 2 14 15 5 01 REVISION 19 2...

Page 1394: ...29 ALL 2 14 25 2 01 REVISION 18 2 15 00 1 01 REVISION 41 ALL except XR 2 15 00 2 01 REVISION 41 2 15 05 1 01 REVISION 41 ALL 2 15 05 2 01 REVISION 41 2 15 05 3 01 del REVISION 41 2 15 05 4 01 del REV...

Page 1395: ...16 10 1 01 REVISION 26 ALL except shuttle 135 2 16 10 2 01 REVISION 20 2 16 10 3 01 OCT 02 2001 2 16 10 4 01 OCT 02 2001 2 16 10 5 01 OCT 02 2001 2 16 10 6 01 OCT 02 2001 2 16 10 7 01 OCT 02 2001 2 1...

Page 1396: ...17 00 2 01 JUN 29 2001 2 17 05 1 01 JUN 29 2001 ALL 2 17 05 2 01 JUN 29 2001 2 17 10 1 01 REVISION 28 ALL 2 17 10 2 01 REVISION 18 2 17 10 3 01 REVISION 28 2 17 10 4 01 REVISION 18 2 17 10 5 01 JUN 29...

Page 1397: ...37 2 17 20 13 01 REVISION 37 2 17 20 14 01 REVISION 37 2 17 20 15 01 REVISION 37 2 17 20 16 01 REVISION 37 2 17 25 1 01 REVISION 37 ALL 2 17 25 2 01 REVISION 38 2 17 25 3 01 REVISION 38 2 17 25 4 01 R...

Page 1398: ...Nav Unit 2 18 09 2 01 MAR 30 2001 2 18 11 1 01 REVISION 33 ALL RMU 2 18 11 2 01 REVISION 33 2 18 11 3 01 REVISION 31 2 18 11 4 01 REVISION 31 2 18 11 5 01 REVISION 31 2 18 11 6 01 REVISION 31 2 18 11...

Page 1399: ...18 11 35 01 REVISION 31 2 18 11 36 01 REVISION 31 2 18 11 37 01 REVISION 33 2 18 11 38 01 REVISION 33 2 18 11 39 01 REVISION 31 2 18 11 40 01 REVISION 31 2 18 11 41 01 REVISION 33 2 18 11 42 01 REVIS...

Page 1400: ...01 REVISION 36 2 18 20 1 01 REVISION 27 Communication Control 2 18 20 2 01 REVISION 19 2 18 20 3 01 AUG 24 2001 2 18 20 4 01 JUN 28 2002 2 18 20 5 01 JUN 28 2002 2 18 20 6 01 JUN 28 2002 2 18 20 7 01...

Page 1401: ...8 21 9 02 JUN 29 2001 2 18 21 10 02 JUN 29 2001 2 18 21 11 02 JUN 29 2001 2 18 21 12 02 JUN 29 2001 2 18 21 1 03 REVISION 33 KHF 1050 2 18 21 2 03 REVISION 33 2 18 22 1 01 MAR 30 2001 3rd VHF COM 2 18...

Page 1402: ...AR 30 2001 2 18 24 5 01 MAR 30 2001 2 18 24 6 01 MAR 30 2001 2 18 24 7 01 AUG 24 2001 2 18 24 8 01 MAR 30 2001 2 18 24 9 01 MAR 28 2002 2 18 24 10 01 MAR 30 2001 2 18 24 1 02 OCT 02 2001 CMU mark iii...

Page 1403: ...1 JUN 29 2001 2 18 28 7 01 JUN 29 2001 2 18 28 8 01 JUN 29 2001 2 18 28 9 01 JUN 29 2001 2 18 28 10 01 JUN 29 2001 2 18 28 11 01 JUN 29 2001 2 18 28 12 01 JUN 29 2001 2 18 28 13 01 JUN 29 2001 2 18 28...

Page 1404: ...6 01 MAR 30 2001 2 18 30 1 02 JUN 28 2002 IRS 2 18 30 2 02 MAR 30 2001 2 18 30 3 02 MAR 30 2001 2 18 30 4 02 DEC 20 2002 2 18 30 5 02 JUN 28 2002 2 18 30 6 02 MAR 30 2001 2 18 30 7 02 MAR 30 2001 2 18...

Page 1405: ...N 28 2002 2 18 35 9 01 JUN 28 2002 2 18 35 10 01 JUN 28 2002 2 18 35 11 01 JUN 28 2002 2 18 35 12 01 JUN 28 2002 2 18 35 13 01 AUG 24 2001 2 18 35 14 01 JUN 28 2002 2 18 35 15 01 REVISION 29 2 18 35 1...

Page 1406: ...8 01 MAR 30 2001 2 18 40 9 01 MAR 30 2001 2 18 40 10 01 MAR 30 2001 2 18 40 11 01 MAR 30 2001 2 18 40 12 01 MAR 30 2001 2 18 40 13 01 MAR 30 2001 2 18 40 14 01 MAR 30 2001 2 18 40 15 01 MAR 30 2001 2...

Page 1407: ...38 2 18 45 19 01 REVISION 38 2 18 45 20 01 REVISION 38 2 18 45 21 01 REVISION 38 2 18 45 22 01 REVISION 38 2 18 45 23 01 REVISION 38 2 18 45 24 01 REVISION 38 2 18 45 25 01 REVISION 38 2 18 45 26 01...

Page 1408: ...1 REVISION 39 2 18 75 15 01 REVISION 39 2 18 75 16 01 REVISION 39 2 18 75 17 01 REVISION 39 2 18 75 18 01 REVISION 39 2 18 75 19 01 REVISION 39 2 18 75 20 01 REVISION 39 2 18 80 1 01 REVISION 38 IFF 2...

Page 1409: ...ION 36 2 19 10 11 01 REVISION 36 2 19 10 12 01 REVISION 40 2 19 10 13 01 REVISION 40 2 19 10 14 01 REVISION 36 2 19 10 15 01 REVISION 36 2 19 10 16 01 REVISION 36 2 19 15 1 01 REVISION 36 ALL 2 19 15...

Page 1410: ...ne certification other Asterisk indicates pages revised added or deleted by the current revision REVISION 41 2 LEP Page 41 Code 105 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 2 19 2...

Page 1411: ...LIST OF EFFECTIVE PAGES AIRPLANE OPERATIONS MANUAL 2 LEP Page 42 Code 105 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 1412: ...GS 2 3 EMERGENCY EQUIPMENT DELETED 2 4 CREW AWARENESS 2 5 ELECTRICAL 2 6 LIGHTING 2 7 FIRE PROTECTION 2 8 FUEL 2 9 AUXILIARY POWER UNIT 2 10 POWERPLANT 2 11 HYDRAULIC 2 12 LANDING GEAR AND BRAKES 2 13...

Page 1413: ...TABLE OF CONTENTS AIRPLANE OPERATIONS MANUAL 2 TOC Page 2 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1414: ...ode 01 SECTION 2 01 AIRPLANE DESCRIPTION TABLE OF CONTENTS Page Block Introduction 2 01 00 Airplane Description 2 01 00 Cockpit Arrangement 2 01 00 Interior Arrangement 2 01 00 Main Glareshield Panels...

Page 1415: ...unted turbofan engines The tricycle landing gear is all retractable with twin tires in each leg A glass cockpit panel has been developed with highly integrated on board avionics thus allowing pilots t...

Page 1416: ...5187 11435 145STD 19200 42328 18700 41226 17100 37698 4174 9200 145EU 19990 44070 18700 41226 17100 37698 4174 9200 145ER 20600 45414 18700 41226 17100 37698 4174 9200 145EP 20990 46275 18700 41226 17...

Page 1417: ...AIRPLANE DESCRIPTION AIRPLANE OPERATIONS MANUAL 2 01 00 Page 4 Code 01 JUNE 28 2002 THREE VIEW DRAWING EMB 145 MODELS...

Page 1418: ...AIRPLANE OPERATIONS MANUAL AIRPLANE DESCRIPTION DECEMBER 20 2002 2 01 00 Page 4A Code 01 THREE VIEW DRAWING EMB 145 XR MODEL...

Page 1419: ...AIRPLANE DESCRIPTION AIRPLANE OPERATIONS MANUAL 2 01 00 Page 4B Code 01 DECEMBER 20 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1420: ...AIRPLANE OPERATIONS MANUAL AIRPLANE DESCRIPTION JUNE 28 2002 2 01 00 Page 5 Code 01 THREE VIEW DRAWING EMB 135 MODELS...

Page 1421: ...AIRPLANE DESCRIPTION AIRPLANE OPERATIONS MANUAL 2 01 00 Page 6 Code 01 JUNE 28 2002 THREE VIEW DRAWING ERJ 140 MODELS...

Page 1422: ...AIRPLANE OPERATIONS MANUAL AIRPLANE DESCRIPTION JUNE 28 2002 2 01 00 Page 7 Code 01 COCKPIT ARRANGEMENT...

Page 1423: ...AIRPLANE DESCRIPTION AIRPLANE OPERATIONS MANUAL 2 01 00 Page 8 Code 01 JUNE 28 2002 INTERIOR ARRANGEMENT CROSS SECTION TYPICAL...

Page 1424: ...AIRPLANE OPERATIONS MANUAL AIRPLANE DESCRIPTION SEPTEMBER 29 2000 2 01 05 Page 1 Code 01 MAIN GLARESHIELD PANELS TYPICAL I...

Page 1425: ...AIRPLANE DESCRIPTION AIRPLANE OPERATIONS MANUAL 2 01 05 Page 2 Code 01 SEPTEMBER 29 2000 CONTROL PEDESTAL TYPICAL I...

Page 1426: ...AIRPLANE OPERATIONS MANUAL AIRPLANE DESCRIPTION SEPTEMBER 29 2000 2 01 05 Page 3 Code 01 MAIN GLARESHIELD PANELS TYPICAL II...

Page 1427: ...AIRPLANE DESCRIPTION AIRPLANE OPERATIONS MANUAL 2 01 05 Page 4 Code 01 JUNE 28 2002 CONTROL PEDESTAL TYPICAL II...

Page 1428: ...AIRPLANE OPERATIONS MANUAL AIRPLANE DESCRIPTION SEPTEMBER 29 2000 2 01 10 Page 1 Code 01 OVERHEAD PANEL TYPICAL...

Page 1429: ...AIRPLANE DESCRIPTION AIRPLANE OPERATIONS MANUAL 2 01 10 Page 2 Code 01 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1430: ...AIRPLANE OPERATIONS MANUAL AIRPLANE DESCRIPTION SEPTEMBER 29 2000 2 01 15 Page 1 Code 01 COCKPIT PARTITION TYPICAL...

Page 1431: ...AIRPLANE DESCRIPTION AIRPLANE OPERATIONS MANUAL 2 01 15 Page 2 Code 01 SEPTEMBER 29 2000 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1432: ...t 2 02 25 01 Controls and Indicators 2 02 25 02 Cockpit Passenger Cabin Partition 2 02 27 01 Water and Waste 2 02 30 01 Water 2 02 30 01 Waste 2 02 30 01 Airstair Main Door 2 02 35 01 EICAS Message 2...

Page 1433: ...Controls and Indicators 2 02 55 02 Audio System 2 02 55 08 Telephone System 2 02 60 01 Cockpit Security Door 2 02 65 01 Door Description 2 02 65 02 Security Door Placards 2 02 65 04 Video Surveillance...

Page 1434: ...e copilot s seat A switch installed in the seat allows height adjustment which is performed by an electrical actuator In case of electrical actuator malfunction height adjustment may also be accomplis...

Page 1435: ...ided the airplane is energized 3 BACKREST INCLINATION ADJUSTMENT BUTTON Pressing the button allows the occupant to select the required inclination by pressure exerted upon the backrest Releasing the b...

Page 1436: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 05 Page 3 Code 01 PILOT SEAT CONTROLS...

Page 1437: ...tion best suited for control column actuation The seat should be moved up or down until the pilot s line of sight reaches the same horizontal plane of a sight device made up of two white spheres and a...

Page 1438: ...ENT Toggle switches installed on the pilot and copilot s panels allows rudder pedals adjustment which is performed by electric actuators Setting the switch up or down signals the actuator to move the...

Page 1439: ...s located behind and between the pilot seats When in use it lies in front of the cockpit door Stow it by folding and rotating away from the door area against the right side of the cockpit partition be...

Page 1440: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 05 Page 7 Code 01 OBSERVER SEAT...

Page 1441: ...ase of loss of visibility through the windshield or for cockpit emergency evacuation Placing respective pilot seat to the aftmost position makes for easier window removal A yellow pin protrudes near t...

Page 1442: ...at the cockpit partition close to the main door The seat is of the fold away type to prevent passageway blockage An optional second flight attendant seat is available at the aft end of the aisle in fr...

Page 1443: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 10 Page 2 Code 01 OCTOBER 02 2001 AFT FLIGHT ATTENDANT SEAT...

Page 1444: ...er cabin divider opposite the forward attendant seat in the entry area This panel provides controls and indications for some functions of the Lighting System Air Conditioning temperature control Atten...

Page 1445: ...lights and attendant call lights The associated attendant call chimes are also activated 3 PSU RESET BUTTON When pressed after test allows resetting all PSUs to the initial state 4 CALL RESET BUTTON W...

Page 1446: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 15 Page 3 Code 01 FORWARD ATTENDANT CONTROL PANEL OPTION 1 AFT ATTENDANT CALL PANEL...

Page 1447: ...lights and attendant call lights The associated attendant call chimes are also activated 3 PSU RESET BUTTON When pressed after test allows reseting all PSUs to the initial state 4 CALL RESET BUTTON W...

Page 1448: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 15 Page 5 Code 01 FORWARD ATTENDANT CONTROL PANEL OPTION 2 AFT ATTENDANT CALL PANEL...

Page 1449: ...lights and attendant call lights The associated attendant call chimes are also activated 3 PSU RESET BUTTON When pressed after test allows reseting all PSUs to the initial state 4 CALL RESET BUTTON W...

Page 1450: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 15 Page 7 Code 01 FORWARD ATTENDANT CONTROL PANEL OPTION 3 AFT ATTENDANT CALL PANEL...

Page 1451: ...lights and attendant call lights The associated attendant call chimes are also activated 3 PSU RESET BUTTON When pressed after test allows reseting all PSUs to the initial state 4 CALL RESET BUTTON W...

Page 1452: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 15 Page 9 Code 01 FORWARD ATTENDANT CONTROL PANEL OPTION 4 AFT ATTENDANT CALL PANEL...

Page 1453: ...0 Code 01 OCTOBER 02 2001 ENTRANCE PANELS The Entrance Panels are located in the entry area and provides main door control and indication and courtesy lights control NOTE The Interior Main Door Contro...

Page 1454: ...different ways and can be equipped with different optional equipment to facilitate and provide an appropriate flight service to the passengers The following items can equip the galley Switches and Cir...

Page 1455: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 20 Page 2 Code 01 OCTOBER 02 2001 GALLEY STANDARD...

Page 1456: ...ed turns on or off the galley area lighting 2 AREA LIGHTING BRIGHT DIM BUTTON When alternately pressed selects the bright or dim mode for galley area lighting 3 LEFT AND RIGHT LIQUID CONTAINER BUTTON...

Page 1457: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 20 Page 4 Code 01 OCTOBER 02 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1458: ...ciated control button at each passenger seat Passenger information sign informing the passenger of NO SMOKING and FASTEN SEAT BELTS instructions Pushbutton and indicator for attendant call Air gasper...

Page 1459: ...ed chime will be heard in all cabin loudspeakers The PA indication located on the Attendant Control Panel will illuminate The associated zone attendant call annunciator will illuminate to provide easy...

Page 1460: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 25 Page 3 Code 01 PASSENGER SERVICE UNIT...

Page 1461: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 25 Page 4 Code 01 OCTOBER 02 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1462: ...le optional allows the cockpit occupants to see through the door assembly The locking latch assembly engages a striker on the LH partition to secure the door when it is closed The cockpit passenger ca...

Page 1463: ...RNESS ASSEMBLY LOCKING LATCH ASSEMBLY STRIKER BLOW OUT PANEL ASSEMBLY FLOOR BRACKET COCKPIT DOOR ASSEMBLY ATTACHMENT HARDWARE STRAP ASSEMBLY RH PARTITION BLUE STERILE LIGHT LH PARTITION EM145AOM022058...

Page 1464: ...tion of the lavatory A water service control panel on the lower rear right side of the wing to fuselage fairing allows the supply of water to the tank and to draining it if necessary WASTE The waste s...

Page 1465: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 30 Page 2 Code 01 REVISION 27 WASTE AND WATER SYSTEM SCHEMATIC...

Page 1466: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 30 Page 3 Code 01 LAVATORY...

Page 1467: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 30 Page 4 Code 01 OCTOBER 02 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1468: ...spectively The door may also be closed and locked raising it manually by an outside ground attendant and actuating either the inner or the outer handle An alternative opening valve is provided in the...

Page 1469: ...uminates when the main door actuator hydraulic line remains pressurized after door closing In this case the main door is hydraulically blocked NOTE The BLOCKED inscription may momentary illuminate whe...

Page 1470: ...ISION 38 2 02 35 Page 3 Code 01 AOM 145 1114 EM145AOM022017A DGN CLOSE PRESS DOOR CONTROL FWD DOOR 1 2 3 EXTERIOR MAIN DOOR CONTROL PANEL MAIN DOOR ALTERNATIVE OPENING VALVE ENTRANCE DOOR PANEL DOOR C...

Page 1471: ...PMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 35 Page 4 Code 01 REVISION 38 AOM 145 1114 AIRSTAIR DOOR OPERATION INSIDE CABIN NOTE The number of red marks may vary with the airplane configurat...

Page 1472: ...CLEAR OF THE DOOR TRAVEL EM145AOM140010A DGN PRESS DOOR CLOSE FWD DOOR CONTROL TO OPEN TO CLOSE PULL HANDLE OUT LET DOOR COME DOWN OPEN COVER PUSH BUTTON WAIT UNTIL DOOR RAISES TO ITS STOP PUSH DOOR...

Page 1473: ...curtain reduces noise level in the forward passenger cabin area when it is installed NOTE The acoustic curtain must be stowed for takeoff and landing The acoustic curtain should be installed during fl...

Page 1474: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 38 2 02 35 Page 7 Code 01 AOM 145 1114 EM145AOM022088A DGN CURTAIN MAIN DOOR ACOUSTIC CURTAIN...

Page 1475: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 35 Page 8 Code 01 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 1476: ...s door will allow docking at jetway terminals The door opening operation is manual The system is mechanical and the door swings opens laterally and toward the airplane s front end The door movement is...

Page 1477: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 35 Page 2 Code 02 REVISION 32 JETWAY DOOR OPERATION INSIDE CABIN NOTE The number of red marks may vary with the airplane configuration...

Page 1478: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 20 2 02 35 Page 3 Code 02 JETWAY DOOR OPERATION OUTSIDE CABIN...

Page 1479: ...n reduces noise level in the forward passenger cabin area when it is installed NOTE The acoustic curtain must be stowed for takeoff and landing The acoustic curtain should be installed during flights...

Page 1480: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 26 2 02 35 Page 5 Code 02 MAIN DOOR ACOUSTIC CURTAIN...

Page 1481: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 35 Page 6 Code 02 REVISION 26 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1482: ...n be found along the fuselage SERVICE DOOR The service door on the right side of the forward fuselage section is used for galley servicing and cabin cleaning between flights It may also be used as an...

Page 1483: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 40 Page 2 Code 01 REVISION 37 AOM 145 1114 SERVICE DOOR OPERATION...

Page 1484: ...52 0040 Part II and Part III or equipped with an equivalent modification factory incorporated the service door can be locked with a locking pin On ground at pilot discretion the pin can be used but m...

Page 1485: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 40 Page 4 Code 01 REVISION 37 AOM 145 1114 SERVICE DOOR LOCKING PIN...

Page 1486: ...side of the fuselage is manually operated from the outside It is provided by a locking mechanism controlled by an external handle stowed in the lower half of the door The door is provided by depressur...

Page 1487: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 40 Page 6 Code 01 REVISION 37 AOM 145 1114 BAGGAGE DOOR OPERATION...

Page 1488: ...ch is inside the nose landing gear wheel well The rear electronic compartment access hatch is located on the rear right side of the fuselage This hatch provides access to the airplane pressurized area...

Page 1489: ...on the forward right side of the wing to fuselage fairing refer to Section 2 8 Fuel System The opening of the fueling panel access door causes a caution message on Eicas In addition the MFD indicates...

Page 1490: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 37 2 02 40 Page 9 Code 01 AOM 145 1114 ACCESS DOORS AND HATCHES...

Page 1491: ...f the airplane white with squares located along the fuselage to denote the various doors and hatches to be monitored If a door or hatch is ajar the associated graphical square will change from green t...

Page 1492: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 37 2 02 40 Page 11 Code 01 AOM 145 1114 DOORS AND HATCHES INDICATION ON MFD...

Page 1493: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 40 Page 12 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 1494: ...bility which monitors the total electrical current in use at the Outlet Units and if necessary disables or enables the available power outlets If any cabin decompression occurs during the flight the M...

Page 1495: ...r System is only activated or deactivated by releasing or pressing the PC Power Button on the IFE Panel 1 PC POWER BUTTON Enables pushed in or disables pushed out the power supply to the AC outlet uni...

Page 1496: ...cabin The Video System Control Unit VSCU selects the signal and allows image viewing on the Preview Unit before the selected video signal is distributed to the monitors The video and audio outputs wi...

Page 1497: ...uld be activated or deactivated by releasing or pressing the IFE Button on the IFE Panel 1 IN FLIGHT ENTERTAINMENT BUTTON IFE Enables pushed in or disables pushed out the power supply to the In Flight...

Page 1498: ...ITAL AUDIO D I G I T A L DOLBY DIGITAL AUDIO DVD Super VCD VCD MP3 CD PLAYER STANDBY PHONES ON STANDBY PICTURE SELECT FLIGHT DECK CONTROLLER DVD PLAYER VSCU CD CHANGER AIRSHOW DIU PREVIEW MONITOR AUDI...

Page 1499: ...ted to the VSCU Panel headphone jack 2 POWER KEY BUTTON When pressed turns on the VSCU 3 SELECT RIGHT KEY Selects the subsequent channel to be displayed on the preview monitor 4 VOLUME UP KEY Increase...

Page 1500: ...PERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 38 2 02 55 Page 5 Code 01 AOM 145 1114 EM145AOM022036A DGN 8 VSCU Video System POWER SELECT ENTER VOLUME SELECT 7 6 5 4 3 2 1 VIDEO SYSTEM CONTROL U...

Page 1501: ...und speed reaches 100 knots the FDC automatically begins to count down the time to destination and displays the time remaining on the Air Show info page After the system is powered to access the curso...

Page 1502: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 38 2 02 55 Page 7 Code 01 AOM 145 1114 AIRSHOW SEL AIRSHOW SEL 1 2 EM145AOM022033A DGN FLIGHT DECK CONTROLLER PANEL...

Page 1503: ...passenger address to simultaneously override all audio channels The Audio System has four stereo channels These four channels are distributed as follows CD Changer DVD Player Video Cassette Player and...

Page 1504: ...ephone handsets Three handsets are located in the passenger cabin and one in the cockpit An additional input output data port is provided on every handset cradle for a fax machine or other analog devi...

Page 1505: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 60 Page 2 Code 01 REVISION 20 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1506: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 60 Page 3 Code 01 TELEPHONE HANDSET LOCATIONS...

Page 1507: ...power on or off To place a call enter the phone number and press SND To receive a call press SND or lift the handset and press SND To end a call press END 1 OPERATING DISPLAY AND STATUS INDICATOR Pro...

Page 1508: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS OCTOBER 02 2001 2 02 60 Page 5 Code 01 TELEPHONE HANDSET...

Page 1509: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 60 Page 6 Code 01 OCTOBER 02 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1510: ...d to receive is 849 to 851 MHz The telephone handsets contain noise canceling microphones to overcome the aircraft noise environment and the audio is digitized at the handset to further ensure clear c...

Page 1511: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 60 Page 2 Code 02 REVISION 25 TELEPHONE HANDSET AND FAX LOCATIONS...

Page 1512: ...pid decompression Smoke evacuation and penetration Required airflow and Emergency ingress and egress Components of the intrusion resistant cockpit door system include Cockpit door latch striker handle...

Page 1513: ...ABLE position Used by pilots to lock the door only if the main door slide latch is inoperative 3 MAIN DOOR SLIDE LATCH LOCKED position Main door slide latch is locked UNLOCKED position Main door slide...

Page 1514: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 25 2 02 65 Page 3 Code 01 SECURITY DOOR...

Page 1515: ...8 DECOMPRESSION PANEL It is a blow out panel that is partially opened when the pressure sensitive latch is automatically released may be used as a cockpit emergency exit 9 PEEPHOLE Peephole allows cr...

Page 1516: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 25 2 02 65 Page 5 Code 01 SECURITY DOOR PLACARDS...

Page 1517: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 65 Page 6 Code 01 REVISION 25 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1518: ...ch is located on the lavatory door just above the OCCUPIED VACANT display there is an alternative mechanism to unlock the door in case of difficulty to open it from inside the lavatory To unlock the d...

Page 1519: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 70 Page 2 Code 01 REVISION 31 SLIDE LATCH...

Page 1520: ...is an access box that can be used to unlock the door from outside the Lavatory To unlock the door the flight attendant must remove the cover and move the rod upward and downward repeatedly In case of...

Page 1521: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 70 Page 4 Code 01 REVISION 31 LAVATORY SLIDE DOOR POST MOD SB 145 25 0287...

Page 1522: ...AIRPLANE OPERATIONS MANUAL EQUIPMENT AND FURNISHINGS REVISION 31 2 02 70 Page 5 Code 01 LAVATORY BIFOLD DOOR POST MOD SB 145 25 0302...

Page 1523: ...EQUIPMENT AND FURNISHINGS AIRPLANE OPERATIONS MANUAL 2 02 70 Page 6 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 1524: ...ATIONS MANUAL EMERGENCY EQUIPMENT DECEMBER 20 2002 2 03 00 Page 1 Code 01 SECTION 2 03 EMERGENCY EQUIPMENT This section has been removed from this volume For emergency information refer to Section 1 1...

Page 1525: ...EMERGENCY EQUIPMENT AIRPLANE OPERATIONS MANUAL 2 03 00 Page 2 Code 01 DECEMBER 20 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1526: ...essages 2 04 10 03 EICAS Message Dictionary 2 04 10 04 Displays Indications 2 04 10 11 Controls and Indicators 2 04 10 12 PFD Presentations 2 04 13 01 Comparison Monitors 2 04 13 01 Caution Annunciato...

Page 1527: ...s 2 04 30 38 Steep Approach Operation 2 04 30 43 Windshear Detection and Escape Guidance System 2 04 35 01 Windshear General Information 2 04 35 01 Windshear Detection 2 04 35 04 Windshear Escape Guid...

Page 1528: ...tall Protection System SPS which shakes the control column if an imminent stall is detected To aid in navigation and approach procedures the airplane is also provided with a Ground Proximity Warning S...

Page 1529: ...either directly or through auxiliary computers The IC 600s are responsible for the interface among the many airplane systems besides managing information presented on the displays Each IC 600 computes...

Page 1530: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS REVISION 23 2 04 05 Page 3 Code 01 AVIONICS INTEGRATION SCHEMATIC...

Page 1531: ...red X RMU 1 automatically displays engine backup page 1 Usually airplane configuration options are set on IC 600 through straps If the number of installed options exceeds the maximum adjustable throu...

Page 1532: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 05 Page 5 Code 01 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1533: ...and copilot panel One EICAS display on the center panel In addition the Radio Management Unit RMU displays on the control pedestal forward panel may be used as a back up for the main panel displays Th...

Page 1534: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 05 Page 7 Code 01 AIRPLANE DISPLAYS...

Page 1535: ...nformation For further information on these parameters refer to Sections 2 17 Flight Instruments 2 18 Navigation and Communication and 2 19 Autopilot The PFD is divided into sections each one presenti...

Page 1536: ...ERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 05 Page 9 Code 01 NOTE Number inside boxes refer to Operations Manual Section where information concerning the associated item can be found PFD DISPLAY...

Page 1537: ...operate in three different presentation modes besides the reversionary ones The Map and Plan modes present navigation information For further information on these refer to Section 2 18 Navigation and...

Page 1538: ...ERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 05 Page 11 Code 01 NOTE Number inside boxes refer to Operations Manual Section where information concerning the associated item can be found MFD DISPLA...

Page 1539: ...sented after warning messages Advisory messages cyan colored and presented after caution messages For further information on engine indications presented in the upper left corner refer to Section 2 10...

Page 1540: ...PERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 05 Page 13 Code 01 NOTE Number inside boxes refer to Operations Manual Section where information concerning associated item can be found EICAS DISPLAY...

Page 1541: ...or each radio NAV and COMM transponder and TCAS In case of failure of the main panel displays the RMU may be selected to present navigation engine or systems information as well as some EICAS messages...

Page 1542: ...ltitude vertical speed scales flight director mode autopilot and yaw damper status MFD presents takeoff page system menu and navigation data in Map format This information is supplied as follows MFD 1...

Page 1543: ...supplying all displays with four different buses two DC Buses and two Essential buses Furthermore each pair of duplicated displays PFDs MFDs and RMUs are supplied by different buses one for each disp...

Page 1544: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 05 Page 17 Code 01 DISPLAYS SUPPLYING SCHEMATIC...

Page 1545: ...are not matching DAU 1 2 A FAIL Associated DAU channel A has failed CAUTION DAU AC ID MISCMP Mismatch between DAU 1 and DAU 2 configuration inputs regarding aircraft type IC 1 2 OVERHEAT Associated te...

Page 1546: ...the IM 600 modules except those considered in the CHK IC CONFIG logic ADVISORY DAU 1 2 B FAIL Associated DAU channel B has failed DAU 1 2 REVERSION Associated DAU has been commanded to operate with ch...

Page 1547: ...n refer to item TCAS presented in this section If TCAS is already selected pressing the button restores the previously selected system page 5 WEATHER RADAR BUTTON Selects weather radar information to...

Page 1548: ...e MFD For further information on this page refer to Sections 2 14 Pneumatics Air Conditioning and Pressurization and Section 2 16 Oxygen 4 FUEL SYSTEM PAGE BUTTON Selects the fuel system page to be pr...

Page 1549: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 05 Page 22 Code 01 DECEMBER 20 2002 MFD BEZEL BUTTON MENU TREE...

Page 1550: ...on this menu refer to Section 2 18 Navigation and Communication 4 AIRPORT AND NAVIGATION AIDS BUTTON Provides selection and toggling of airport and navigation aids displays on the MFD For further info...

Page 1551: ...s on the MFD the information normally presented on the EICAS 2 ADC BUTTON Changes the ADC information from the on side ADC to the cross side ADC A striped bar illuminates inside the button to indicate...

Page 1552: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 05 Page 25 Code 01 REVERSIONARY PANEL...

Page 1553: ...NE 28 2002 EICAS REVERSIONARY PANEL 1 DAU REVERSIONARY BUTTON Allows channel B of associated DAU to supply both IC 600s A striped bar is illuminated inside the button to indicate that it is pressed an...

Page 1554: ...27 Code 01 PRIMARY FLIGHT DISPLAY 1 SYMBOL GENERATOR REVERSION ANNUNCIATION Indicates that a symbol generator reversion has been selected on the reversionary panel Presented on both PFDs Labels SG1 f...

Page 1555: ...17 Flight Instruments and 2 18 Navigation and Communication 1 TEST BUTTON On the ground When pressed activates the IC 600s first level test When pressed for more than 6 seconds activates the IC 600s...

Page 1556: ...rformed after the power up BIT as well as autopilot functions PILOT INITIATED BIT A pilot initiated BIT may be commanded by pressing the TEST button in the displays control panel This test may be comm...

Page 1557: ...ll comparison monitors all marker beacons and windshear annunciation Indications presented as invalid pitch and roll vertical and lateral deviations baro correction vertical speed set digital readout...

Page 1558: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 05 Page 31 Code 01 PFD TEST INDICATIONS FIRST LEVEL...

Page 1559: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 05 Page 32 Code 01 JUNE 28 2002 PFD TEST INDICATIONS SECOND LEVEL...

Page 1560: ...emoved heading source TCAS weather patch drift bug wind vector heading select bug flight plan data airports navaids designator information Indications forced TERRAIN FAIL EICAS CHK WX TERRAIN MENU INO...

Page 1561: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 05 Page 34 Code 01 JUNE 28 2002 MFD TEST INDICATIONS...

Page 1562: ...ations forced the crew awareness field will be filled with a X Indications presented as invalid landing gear status N1 N2 ITT fuel flow and quantity oil pressure temperature and quantity vibration for...

Page 1563: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 05 Page 36 Code 01 JUNE 28 2002 EICAS TEST INDICATIONS...

Page 1564: ...ions such as the windshield heating the GPU the ice protection wing and stab and the APU bleed buttons which are illuminated under normal operating conditions Some systems also provide indicating ligh...

Page 1565: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 10 Page 2 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1566: ...When the message is generated it is displayed blinking at the top of the associated group To stop blinking press the associated master button on the glareshield Advisory messages will stop blinking a...

Page 1567: ...on the ground for 3 seconds or more after 1 minute IC 600 RESULTS SELF CHECK The results of both IC 600 computations are continuously compared to check for any inconsistency between both sides A dedi...

Page 1568: ...ECK IC 1 2 SW 2 C CHECK PFD 1 2 2 C CHK IC CONFIG 2 C DAU AC ID MISCMP 2 C DAU 1 2 A FAIL 2 C DAU 1 2 ENG MISCOMP 2 C DAU 1 2 SYS MISCOMP 2 C DAU 1 2 WRN MISCOMP 2 C GPWS INOP 3 C IC BUS FAIL 2 2 4 C...

Page 1569: ...US 2 C GEN 1 2 3 4 OVLD 2 C SHED BUS 1 2 OFF 2 A GEN 1 2 3 4 BRG FAIL 2 2 6 LIGHTING C EMERG LT NOT ARMD 2 W APU FIRE 3 W BAGG SMOKE 2 W ENG 1 2 FIRE 3 2 7 W LAV SMOKE 2 FIRE C APU EXTBTL INOP 2 PROTE...

Page 1570: ...APU OIL LO PRESS 2 W ATTCS FAIL 5 W E1 2 ATTCS NO MRGN 2 W E1 2 OIL LOW PRESS 2 W E1 2 LOW N1 2 W ENG 1 2 OUT 1 C E1 2 ATS SOV OPN 2 C E1 2 CTL A B FAIL 2 C E1 2 CTL FAIL 2 C E1 2 EXCEEDANCE 2 C E1 2...

Page 1571: ...INOP 1 GEAR AND C EMRG BRK LO PRES 1 BRAKES C LG AIR GND FAIL 3 C STEER INOP 2 C NLG UPDOOR OPN 2 C BRAKE DEGRADED 1 W PIT TRIM 1 2 INOP 2 W PTRIM MAIN INOP 2 W PTRIM BACKUP INOP 2 C AIL SYS 1 2 INOP...

Page 1572: ...D 1 2 VLV CLSD 2 A HI ALT LDG T O 2 A CROSS BLD OPEN 2 A PACK 1 2 VLV CLSD 2 W ICE COND A I INOP 2 C A ICE LOW CAPACITY 3 C A ICE SWITCH OFF 2 C AOA 1 2 HEAT INOP 2 C E1 2 A ICE FAIL 2 C ICE DET1 2 FA...

Page 1573: ...2 2 18 A A lll NOT AVAIL 3 NAVIGATION A AHRS 1 2 ALN 2 AND A AHRS 1 2 ATT MODE 2 COMMUNICATION A AHRS 1 2 BASIC MODE 2 A AHRS 1 2 EXC MOTION 2 A AHRS 1 2 NO MAG HDG 4 A AHRS 1 2 NO PPOS 1 A AHRS 1 2 O...

Page 1574: ...ly into the out of range area Pointers are removed if the parameter signal becomes invalid For some parameters scale may also be removed in this condition Scale and pointer are not presented for some...

Page 1575: ...the warning messages and stops the associated blinking when pressed A red light blinks inside the button when a new warning message is displayed on the EICAS 2 MASTER CAUTION BUTTON Acknowledges the...

Page 1576: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 10 Page 13 Code 01 GLARESHIELD PANEL GLARESHIELD PANEL OPTIONAL...

Page 1577: ...01 JUNE 28 2002 EICAS BEZEL 1 MESSAGE SCROLLING KNOB To be used when displayed EICAS messages can not be presented at once By rotating the knob clockwise advances through EICAS messages Rotated count...

Page 1578: ...28 2002 2 04 10 Page 15 Code 01 PRIMARY FLIGHT DISPLAY 1 EICAS CHECK SUM FAIL COMPARISON MONITOR DISPLAY Color amber Label CAS MSG Displayed when the number of active EICAS messages in each IC 600 is...

Page 1579: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 10 Page 16 Code 01 JUNE 28 2002 EICAS DISPLAY EICAS MESSAGES EXAMPLE...

Page 1580: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS JUNE 28 2002 2 04 10 Page 17 Code 01 RMU DISPLAY RMU MESSAGES EXAMPLE...

Page 1581: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 10 Page 18 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1582: ...e when pitch attitude data differs by more than 5 2 ALT ALTITUDE Displayed in the upper right corner of the altitude tape when altitude data differs by more than 200 ft 3 HDG HEADING Displayed to the...

Page 1583: ...ter 1 failure Radio Altitude source is RA2 9 IAS AIRSPEED If the on side and cross side calibrated airspeed differ by 5 kt or more for longer than 2 seconds it is displayed in the upper left corner of...

Page 1584: ...3 Code 01 AOM 145 1114 EM145AOM040023A DGN OO I A S O 1O 1O 1O 1O 2O 2O A L T HDG ALT 7O 15OO 1O 2O 4O OO 3O 17 IN 169 M 8O 6O 4 2 R 1 132 124 11O LOC RA CAS MSG 5 PIT 2OO RA 2O 2O HDG 1 2 3 7 8 9 10...

Page 1585: ...s for more information 3 GND PROX When the EGPWS indicates a caution conditions GND PROX is displayed in the upper right of the ADI sphere The following aural alerts are considered cautionary SINK RAT...

Page 1586: ...their normal onside attitude source there is no attitude source annunciator If the pilot and copilot have selected the same attitude source that attitude source ATT1 or ATT2 is annunciated to the low...

Page 1587: ...left of the attitude sphere on both PFDs 14 WDSHEAR When the windshear detection system detects windshear WDSHEAR is displayed to the upper left of the attitude sphere The annunciator flashes for 10 s...

Page 1588: ...GN BARO IN HPA STD NM W 24 30 0 2 1 1 2 3 33 N 3 S E 6 1 2 15 2 1 HDG IN CRS 3 AP YD I A S A L T ATT FAIL ATT O I M 200 RA M A O A RA LOC CAS MSG VOR1 GSPD KTS V S HDG FAIL HDG FD FAIL ADC2 SG2 GND PR...

Page 1589: ...scales If the digital Mach display fails the digital readout is replaced with amber dashes In the case of the vertical speed the current value pointer is removed a boxed VS is displayed inside the sc...

Page 1590: ...ISION 39 2 04 13 Page 9 Code 01 AOM 145 1114 EM145AOM040025A DGN BARO IN HPA STD NM W 24 30 0 2 1 1 2 3 33 N 3 S E 6 1 2 15 2 1 HDG IN CRS 3 ATT FAIL 100 RA M ILS2 GSPD KTS V S HDG FAIL PULL UP RA 1 3...

Page 1591: ...DIRECTOR MODE ANNUNCIATORS The VS MACH PIT ASEL TO CLB ALT WSHR SPD DES GS IAS and GA mode annunciators are displayed Armed modes are displayed in white while captured modes are displayed in green an...

Page 1592: ...1114 EM145AOM040027A DGN 1 LOC HDG IAS GS AP YD 2 3 20 20 10 10 10 10 20 20 200 0 3 2 1 1 2 3 1000 51 M 240 220 180 160 470 M 359 CRS ILS1 NM 25 HDG TTG 5MIN 12400 12900 IN 12700 29 92 120 00 0 0 1 ST...

Page 1593: ...nect in CAT II TCS White Steady while TCS switch is pushed Touch control steering TKNB Amber Steady TURN knob is out of detent 2 YAW DAMPER ANNUNCIATORS MESSAGE COLOR TYPE STATUS YD Green Steady Engag...

Page 1594: ...radio altitude is equal to or less than the set value MIN is displayed in amber inside the box and it flashes for 10s 5 MARKER BEACON ANNUNCIATOR A cyan O represents the outer an amber M represents th...

Page 1595: ...H 25 HDG GSPD 14OOO 145OO IN OO 29 92 145 OO O O 1 LNAV VS 26O WX 5O 3 5 28O 26O 24 FMS APP KDVT DR VOR1 ADF2 TGT 245KTS MAG2 HDG MSG TCAS TEST 3OOO 2OO RA 359 41O 12 5 ATT2 LOC SXTK FHDG RA CAS MSG M...

Page 1596: ...elected as navigation source and yellow when the same navigation source on both sides or secondary NAV source is selected 2 MEASUREMENTS One of the annunciators TTG in white ET in green or GSPD in gre...

Page 1597: ...NAVIGATION SOURCE ANNUNCIATORS One of the Navigation Source Annunciators VOR1 VOR2 ILS1 ILS2 or FMS is displayed 7 COURSE POINTER AND DIGITAL DISPLAY If short range NAV is selected the annunciator CRS...

Page 1598: ...114 EM145AOM040029A DGN 1 LOC CAT2 AP YD 20 20 10 10 10 10 20 20 200 0 3 2 1 1 2 3 1000 51 M 240 220 180 160 470 M 359 CRS ILS1 NM 25 HDG TTG 5MIN 12400 12900 IN 12700 29 92 120 00 0 0 1 STD BARO IN H...

Page 1599: ...n amber is displayed in amber and flashes until the FMS condition is cleared 3 WEATHER RADAR MODE ANNUNCIATOR The mode annunciators are described below ANNUNCIATOR COLOR R T MODE FPLN green Flight pla...

Page 1600: ...ngle field 4 WEATHER RADAR TGT VAR ANNUNCIATORS When the target alert mode is armed the message TGT in green appears It turns amber when a potentially dangerous target is detected This indicates that...

Page 1601: ...r RNAV FMS approaches the annunciator is displayed steady and for GPS approaches the annunciator flashes for ten seconds The table below shows the Full scale Deviation for FMS Terminal and Approach Mo...

Page 1602: ...H 25 HDG GSPD 14OOO 145OO IN OO 29 92 145 OO O O 1 LNAV VS 26O WX 5O 3 5 28O 26O 24 FMS APP KDVT DR VOR1 ADF2 TGT 245KTS MAG2 HDG MSG TCAS TEST 3OOO 2OO RA 359 41O 12 5 ATT2 LOC SXTK FHDG RA CAS MSG M...

Page 1603: ...described below 1 TCAS STATUS ANNUNCIATOR Annunciator Color TCAS Status TA ONLY white TCAS is in traffic advisory mode only TCAS OFF white TCAS is off TCAS TEST white TCAS is in self test TCAS FAIL am...

Page 1604: ...ays are flagged All pointers scales are flagged All heading bugs pointers are removed Flight director command cue is removed Radio altimeter digital readout displays radio altimeter self test value Th...

Page 1605: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 13 Page 24 Code 01 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 1606: ...nt forms and indicate some notable airplane events sometimes in unison with voice messages AURAL WARNING UNIT In order to generate messages and tones the Aural Warning Unit AWU receives signals from t...

Page 1607: ...sory Associated with minor malfunctions or failures that lead to loss of redundancy or degradation of the affected system s performance Information A remarkable event has occurred AURAL WARNINGS ANNUN...

Page 1608: ...D NO Landing gear not locked down for landing 7 Attenson 3 LANDING GEAR NO EMERGENCY Cabin altitude above 10000 ft Normal Mode Operation or Cabin altitude above 14500 ft HI ALT Mode Operation only for...

Page 1609: ...NOTE 1 Messages are generated outside the AWU For further details refer to the associated system description 2 TCAS resolution advisory warning can not be canceled 3 For airplanes Post Mod SB 145 34...

Page 1610: ...00 ft above or below the selected 1 Horn None Not applicable Power up test detected a failure in one channel of AWU Not applicable None AURAL UNIT ONE CHANNEL NO Associated with incorrect command of p...

Page 1611: ...or further information 2 Applicable to airplanes equipped with HSCU 1009 or 5009 and AWU 5 3 For airplanes Post Mod SB 145 23 0028 4 For airplanes equipped with AWU 5 the altitude alerter is three 290...

Page 1612: ...position Parking brakes are applied Pitch trim is out of the green range Any spoiler panel is deployed More than one aural warning may be generated if more than one condition are met TEST BUTTON A tes...

Page 1613: ...ESS AIRPLANE OPERATIONS MANUAL 2 04 20 Page 2 Code 01 REVISION 23 CONTROLS AND INDICATORS 1 TAKEOFF CONFIGURATION CHECK BUTTON Allows checking the takeoff configuration warning TAKEOFF CONFIGURATION C...

Page 1614: ...tivation regardless of the altitude The basic difference between lower and higher levels is that at higher altitudes the pusher and the shaker speeds are higher due to above mentioned stall protection...

Page 1615: ...or flaps 9 18 and 22 NOTE The first in flight ice detection by any ice detector activates the ice compensation The ice compensation is inhibited during 5 minutes after takeoff The ice compensation is...

Page 1616: ...PANEL STICK SHAKER 1 STICK PUSHER STICK SHAKER 2 AWU AOA 1 CHANNEL 1 CHANNEL 2 AOA 2 RADIO ALTIMETER 1 RADIO ALTIMETER 2 LANDING GEAR POSITION AIR GROUND QUICK DISCONNECT DAU 1 IC 600 1 HSCU HSCU FLAP...

Page 1617: ...ed or is cutout CAUTION SPS ADVANCED Stick shaker and pusher actuation is set to higher speeds due to Flap signal disagreement Failure in at least one SPS channel AHRS or ADC parameters disagree Air G...

Page 1618: ...e button to indicate that it is in the cutout position 2 TEST BUTTON Starts the test sequence as follows Button illuminates Both stick shakers actuate Pusher actuates Button illumination extinguishes...

Page 1619: ...W AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 25 Page 6 Code 01 REVISION 39 AOM 145 1114 EM145AOM042027A DGN 1 STALL PROTECTION CUTOUT 1 CUTOUT 2 TEST TEST CONTROL PEDESTAL 2 STALL PROTECTION SYSTEM PAN...

Page 1620: ...from 10 up to 5 amber for margin between 5 and 2 red for margin below 2 Pitch Limit Indicator as well as the pusher and shaker firing angles are corrected for mach compensation at higher altitudes or...

Page 1621: ...AIRPLANE OPERATIONS MANUAL 2 04 25 Page 8 Code 01 REVISION 39 Pages 9 and 10 deleted AOM 145 1114 EM145AOM042028A DGN PFD 2O 2O 1O 1O 1O 1O 22O 2OO 26O 28O 26O O 24 41O I A S 2 R 1 M 2O 2O 1 2 PRIMARY...

Page 1622: ...to the EGPWS Airplanes equipped with EGPWS version 216 and on incorporates additional features like Peaks Mode Runway Field Clearance Floor Obstacle Alerting and Geometric Altitude The GPWS EGPWS is...

Page 1623: ...be canceled without any restriction Terrain Inhibit Switch It is used in approach mode in airports not covered by an EGPWS database assuring protection against unwanted terrain alerts Some modes may...

Page 1624: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS REVISION 38 2 04 30 Page 3 Code 01 AOM 145 1114 INTENTIONALLY BLANK...

Page 1625: ...S RADIO FLAP GEAR AWU GLIDE SLOPE DEVIATION LOCALIZER DEVIATION COURSE PACKED DISCRETE MAGNETIC HEADING ROLL AND PITCH ANGLE NORMAL AND LONGITUDINAL ACCELERATION ALTITUDE RATE ALTITUDE CORRECTED AND U...

Page 1626: ...GLIDE SLOPE DEVIATION LOCALIZER DEVIATION COURSE PACKED DISCRETE SELECTED TERRAIN RANGE MAGNETIC HEADING ROLL AND PITCH ANGLE NORMAL AND LONGITUDINAL ACCELERATION COMPUTER AND TRUE AIRSPEED ALTITUDE R...

Page 1627: ...Altitude Rate Maximum 2450 ft at 7125 ft min or greater of descent Altitude Rate Penetration of the outer sinkrate boundary will result in Aural message SINK RATE The message will be repeated as long...

Page 1628: ...800 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800 3000 SINKRATE WARNING AREA OVER FLAT TERRAIN OR WATER PULL UP WARNING AREA MINIMUM TERRAIN CLEARANCE ft ALTITUDE RATE ft min DESCENT MODE 1 EXCESS...

Page 1629: ...n airspeed equal or below 220 KIAS 2450 ft at 9800 ft min or greater of Closure Rate for an airspeed equal or above 310 KIAS If the airplane penetrates the Mode 2A envelope the situation results in Au...

Page 1630: ...EA AIRSPEED 220kt AIRSPEED EXPANDS UPPER LIMIT WHEN BETWEEN 220 AND 310 kt ALERT WARNING AREA 30 ft 1220 ft 0 200 400 600 800 1000 1200 1600 1800 2000 2200 2400 2600 2800 1400 0 2000 4000 6000 8000 MI...

Page 1631: ...he Mode 2B envelope with both gear and flaps in the landing configuration the message TERRAIN is sounded If the airplane penetrates the mode 2B envelope with either the landing gear UP or flaps not in...

Page 1632: ...0 1600 1800 2000 2200 2400 2600 MINIMUM TERRAIN CLEARANCE ft STATIC ALERT WARNING ENVELOPE ALERT WARNING AREA 0 2000 4000 6000 8000 10000 789 ft 3000 ft min 2253 ft min 2038 ft min FLAPS UP LOWER CUTO...

Page 1633: ...DON T SINK and GPWS warning message on EICAS for airplanes equipped with GPWS or Amber GND PROX indication on the PFD for airplanes equipped with EGPWS The audio message is only annunciated twice unl...

Page 1634: ...ft LOSS 5 ft LOSS 30 ft ALERT WARNING AREA 0 40 80 120 160 200 240 280 0 200 400 600 800 1000 1200 1400 1600 1800 2000 2200 2400 2600 STATIC ALERT WARNING ENVELOPE MINIMUM TERRAIN CLEARANCE ft ALTITU...

Page 1635: ...equal or higher than 250 KIAS If during cruise the ground is slowly getting closer and the airplane is not in the landing configuration or during approach with an unintentional gear up landing the au...

Page 1636: ...2000 2200 2400 2600 30 ft MINIMUM TERRAIN CLEARANCE ft STATIC ALERT WARNING ENVELOPE COMPUTED AIRSPEED kt 100 200 300 400 500 ft 190 kt 250 kt 1000 ft ALERT WARNING AREA EXPANDED ALERT WARNING AREA 1...

Page 1637: ...and the airplane is not in the landing configuration or during approach with an unintentional gear up landing the aural message TOO LOW TERRAIN will be sounded Once the message is issued an additiona...

Page 1638: ...600 1800 2000 2200 2400 2600 30 ft MINIMUM TERRAIN CLEARANCE ft STATIC ALERT WARNING ENVELOPE COMPUTED AIRSPEED kt 100 200 300 400 250 kt 1000 ft 1000 ft 500 ft 50 ft TOO LOW TERRAIN TOO LOW FLAP 245...

Page 1639: ...O LOW TERRAIN message triggering Minimum 30 ft Maximum 500 ft at 667 ft or greater of radio altitude for an airspeed less or equal or less than 190 KIAS 1000 ft at 1333 ft or greater of radio altitude...

Page 1640: ...WARNING AREA 30 ft ALERT WARNING AREA 0 200 400 600 800 1000 1200 1400 1600 1800 2000 2200 2400 2600 0 200 400 600 800 1000 1200 1400 1600 1800 2000 2200 2400 2600 RADIO ALTITUDE ft MINIMUM TERRAIN CL...

Page 1641: ...The first alert occurs whenever the airplane is more than 1 3 dots below the beam and is called a soft alert because the volume level is reduced A second alert occurs below 300 ft radio altitude with...

Page 1642: ...2 3 4 0 200 400 600 800 1000 1200 1400 1600 1800 2000 2200 2400 2600 150 ft 1 3 DOTS 1000 ft 2 98 DOTS 30 ft 3 68 DOTS SOFT ALERT AREA GLIDE SLOPE 1000 ft GLIDE SLOPE DEVIATION DOTS FLY UP 300 ft MINI...

Page 1643: ...minimums Alerts for excessive roll or bank angle are also provided There are two configurations of EGPWS callouts certified for the EMB 145 family MINIMUMS CALLOUTS ALTITUDE CALLOUTS CONFIGURATION 1 A...

Page 1644: ...get has been reached with the landing gear down Radio altitude for message triggering Minimum 10 ft Maximum 1000 ft Visual indication of minimum target is presented on PFD ALTITUDE CALLOUTS The messag...

Page 1645: ...age triggering for EGPWS Minimum 5 ft Maximum Increases linearly from 30 ft at 10 of bank angle to 150 ft at 40 then from 150 ft at 40 up to 2450 ft at 55 remaining constant at 55 above 2450 ft The au...

Page 1646: ...15 20 25 30 35 40 45 0 100 200 300 400 500 600 700 800 900 1000 1100 1200 1300 150 ft 6 deg LEFT RIGHT ROLL ANGLE deg TERRAIN CLEARANCE ft GPWS MODE 6 SCHEMATIC BANK ANGLE CALLOUT EM145AOM042043B DGN...

Page 1647: ...CF is active during takeoff cruise and final approach and is based on current airplane position nearest runway and radio altitude This alert mode complements the Mode 4 by providing an alert based on...

Page 1648: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS REVISION 38 2 04 30 Page 27 Code 01 AOM 145 1114 EM145AOM042032B DGN 700 ft 400 ft TCF ALERT AREA 1 2 NM TO 2 NM 4 NM 12 NM 15 NM TCF ALERT ENVELOPE...

Page 1649: ...light crew about potential terrain conflicts The alerts are based mainly on the airplane s current position and barometric altitude information In the event of terrain caution or warning conditions a...

Page 1650: ...and the amber GND PROX indication is displayed on the PFD This is repeated every seven seconds as long as the airplane is still in the caution envelope When conditions have been met to generate a Terr...

Page 1651: ...sity red dots Terrain that is more than 2000 ft above airplane altitude High density yellow dots Terrain that is between 1000 and 2000 ft above airplane altitude Medium density yellow dots Terrain tha...

Page 1652: ...ft GEAR DOWN 500 ft 1000 ft 2000 ft AIRPLANE ALTITUDE MEDIUM DENSITY GREEN LIGHT DENSITY GREEN BLACK HIGH DENSITY RED HIGH DENSITY YELLOW MEDIUM DENSITY YELLOW EGPWS DISPLAY COLOR CODING N 3 3 O 6 33...

Page 1653: ...hest elevation on top and the lowest on the bottom In the event that there is no appreciable difference in the terrain obstacle elevations only the highest value is displayed The color of the elevatio...

Page 1654: ...n will be displayed as a function of the highest and lowest elevations in view Moreover sea level elevations can be displayed as cyan to simulate water EM145AOM042103B DGN HIGHEST BAND MIDDLE BAND LOW...

Page 1655: ...ected destination runway from the current altitude MSL This feature provides improved alerting for cases where the runway is at a high elevation compared to the terrain below the approach path 1 5 nm...

Page 1656: ...STACLE sounds approximately 45 seconds prior to potencial terrain conflict and the aural OBSTACLE OBSTACLE PULL UP sounds approximately 30 seconds prior to potencial terrain conflict GEOMETRIC ALTITUD...

Page 1657: ...override a lower priority message even if it is already in progress MESSAGE MODE PULL UP 1 and 2 TERRAIN TERRAIN 2 and Terrain Look Ahead PULL UP Terrain Look Ahead TERRAIN 2 MINIMUMS MINIMUMS 6 CAUT...

Page 1658: ...PWS One GPWS envelope associated to Modes 1 to 4 has been penetrated CAUTION GPWS INOP GPWS monitor has detected an internal failure EGPWS TYPE MESSAGE MEANING WARNING GPWS One GPWS envelope associate...

Page 1659: ...YSTEM OVERRIDE BUTTON When pressed inhibits EGPWS in approach mode thus avoiding unwanted terrain alerts in airports not covered by EGPWS database EM145AOM042046C DGN GPWS LG WRN TERRAIN SYS OVRD CUTO...

Page 1660: ...MFD to toggle between the weather radar or terrain to be displayed The ranges allowed are 5 NM 10 NM 25 NM 50 NM 100 NM 200 NM 300 NM 500 NM and 1000 NM When a terrain warning caution condition exist...

Page 1661: ...proach mode TERR N A Amber Lit when EGPWS is uncertain of the airplane s position TERR TEST Red Lit when the self test is activated TERR Center Amber Lit when terrain picture bus fails Airplanes equip...

Page 1662: ...NUAL CREW AWARENESS REVISION 38 2 04 30 Page 41 Code 01 AOM 145 1114 OPEN EM145AOM042048B DGN DOORS REF A ICE OFF ENGINE DOOR TX TGT T O MODE T O 1 REF TO TEMP 25 C O N 3 3 O 6 33 5O 5O FMS TERR 1 2 3...

Page 1663: ...IATIONS Label PULL UP red GND PROX for Ground Proximity amber PULL UP is lit when either modes 1 or 2 have been activated in their more critical situation GND PROX is lit when ground is getting closer...

Page 1664: ...acted to a position other than 45 or airplane lands the STEEP white light extinguishes indicating that the Steep Approach mode is no longer available The pushbutton lower portion has two status lights...

Page 1665: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 30 Page 44 Code 01 REVISION 38 AOM 145 1114 EM145AOM042100B DGN STEEP GREEN AMBER GLARESHIELD PANEL STEEP APPROACH MODE PUSHBUTTON...

Page 1666: ...when the button is pressed with the STEEP light illuminated This means that the Steep Approach mode is engaged With the STEEP light illuminated if the green light does not illuminates when the pushbut...

Page 1667: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 30 Page 46 Code 01 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 1668: ...indshear wind may shift from a tailwind to a headwind or to a downdraft or updraft The consequences may be an abrupt change in airspeed lift and altitude upwards or downwards according to shifting dir...

Page 1669: ...2 Code 01 REVISION 39 AOM 145 1114 EM145AOM042075A DGN FLIGHT DIRECTION WATER LAND UPDRAFT FLIGHT DIRECTION HILL TURBULENCE CLOUD BASE OUTFLOW FRONT OUTFLOW VIRGA OR RAIN DOWN DRAFT HORIZONTAL VORTEX...

Page 1670: ...5 1114 EM145AOM042051A DGN MICROBURST MICROBURST RUNWAY RUNWAY WINDSHEAR EFFECT DURING TAKEOFF RUNWAY GLIDE SLOPE MICROBURST INSTRUMENTS VISUAL MICROBURST MICROBURST SERIES OF HORIZONTAL VERTICES FLIG...

Page 1671: ...On airplanes equipped with EGPWS an aural message CAUTION WINDSHEAR is also triggered Windshear Caution indications remain on for as long as the airplane remains exposed to an increasing headwind and...

Page 1672: ...35 Page 5 Code 01 AOM 145 1114 EM145AOM042076A DGN 3000 UPDRAFT FEET MIN 2000 1000 6 4 2 0 0 2 4 6 1000 2000 3000 DOWNDRAFT FEET MIN DECREASING HEADWIND KNOT SEC INCREASING HEADWIND KNOT SEC AMBER RE...

Page 1673: ...detected Automatically when Thrust Levers Angle is above 78 and a decreasing performance windshear is detected windshear warning When the windshear escape guidance mode is engaged a green WSHR indicat...

Page 1674: ...path angle A nominal flight path angle is used to allow an airspeed raise during an increasing performance windshear in anticipation of a decreasing performance windshear and also to minimize altitud...

Page 1675: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 35 Page 8 Code 01 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 1676: ...OSITION RADIO ALTITUDE PFD 1 WS CAUTION WS WARNING IC 600 1 EICAS WS INOP GO AROUND BUTTON PFD 2 WS CAUTION WS WARNING IC 600 2 AWU WINDSHEAR CARD CORRECTED BARO ALTITUDE ADC INERTIAL VERTICAL SPEED I...

Page 1677: ...RY FLIGHT DISPLAY 1 WINDSHEAR INDICATION Indicates that a windshear has been detected Color amber or red depending on windshear severity 2 ESCAPE GUIDANCE MODE ENGAGEMENT ANNUNCIATION Indicates the Wi...

Page 1678: ...FD 12O 1OO 18O 16O 2O 2O 1O 1O PFD 12O 1OO 16O 18O 16O O 14 2O 2O ROL WSHR WDSHEAR 1 2 3 4 1O 1O 2O 2O 1O 1O 2O 2O 1O 1O ROL WSHR WDSHEAR 1 2 3 4 2O 2O 1O 1O 1O 1O 2O 2O 1O 1O 1O 1O 12O 1OO 18O 16O 12...

Page 1679: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 35 Page 12 Code 01 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 1680: ...the TCAS software version 6 04 The altitude separation thresholds for issuing Traffic Advisory TA and Resolution Advisory RA between FL300 and FL420 are reduced for compatibility with RVSM flight ope...

Page 1681: ...hether or not it may become a target To determine that an alert zone is established based on separation and speeds of both airplanes The size of the alert zone is not distance based but rather is base...

Page 1682: ...ndicate the intruder s relative position altitude and danger level A voice message is generated to help the pilots in taking the most suitable action The PFD provides indication of the recommended ver...

Page 1683: ...the way some parameters are presented For airplanes Post Mod SB 145 34 0089 or Post Mod SB 145BAF 34 0006 or equipped with an equivalent modification factory incorporated the Mode S Elementary Surveil...

Page 1684: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS REVISION 36 2 04 40 Page 5 Code 01 AOM 145 1114 TCAS SCHEMATIC...

Page 1685: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 40 Page 6 Code 01 REVISION 36 AOM 145 1114 TCAS PROTECTED AREAS...

Page 1686: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS REVISION 36 2 04 40 Page 7 Code 01 AOM 145 1114 TCAS SITUATIONS...

Page 1687: ...ly MAINTAIN VERTICALSPEED MAINTAIN Maintain the vertical speed indicated on the VSI TCAS software version 7 0 only MAINTAIN VERTICAL SPEED CROSSING MAINTAIN Maintain the vertical speed indicated on th...

Page 1688: ...AGL while descending and below 1650 ft AGL while climbing CLIMB CLIMB NOW After a descent advisory TCAS detected a changing situation that requires the need to climb DESCEND DESCEND NOW After a climb...

Page 1689: ...raffic advisory and resolution advisory modes are selected Refer to Section 2 18 Navigation and Communication for further details 2 TCAS CONTROL SIDE IDENTIFICATION Indicates which TCAS display MFD 1...

Page 1690: ...L green With the TA display set to AUTO the operational TCAS altitude band will be from 1200 ft below to 1200 ft above the airplane With the TA display set to MANUAL the operational TCAS altitude band...

Page 1691: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 40 Page 12 Code 01 REVISION 36 AOM 145 1114 RMU RADIO PAGE...

Page 1692: ...ng on whether the intruder is above or below the airplane FL cyan Intruder s altitude is displayed as its flight level This selection automatically reverts to REL after 20 seconds 2 TA DISPLAY AUTO Tr...

Page 1693: ...CREW AWARENESS AIRPLANE OPERATIONS MANUAL 2 04 40 Page 14 Code 01 REVISION 36 AOM 145 1114 RMU ATC TCAS CONTROL PAGE...

Page 1694: ...for 7 seconds the RMU TST button A white TCAS TEST message is presented on the MFDs and PFDs A TCAS TEST aural warning sounds The Master Warning lights flash NOTE Some airplanes don t have the Master...

Page 1695: ...ntruder whose bearing cannot be determined Up to two lines may be displayed indicating the kind of advisory its distance relative altitude and whether it is climbing or descending in excess of 500 ft...

Page 1696: ...rplane intruder s altitude is displayed below its symbol If intruder is above the airplane intruder s altitude is displayed above its symbol 7 RESOLUTION ADVISORY INDICATION Indicated by a solid red s...

Page 1697: ...14 12 TCAS BAND SELECTED Indicates whether the selected band for TCAS is below or above 13 TCAS MODE ANNUNCIATIONS Indicates current TCAS mode Colors and labels are as follows in the order of priority...

Page 1698: ...AIRPLANE OPERATIONS MANUAL CREW AWARENESS REVISION 36 2 04 40 Page 19 Code 01 AOM 145 1114 MULTI FUNCTION DISPLAY...

Page 1699: ...lict Green range displayed along the scale indicates the range of vertical speeds to be attained to avoid a conflict situation Red range displayed along the scale indicates the range of vertical speed...

Page 1700: ...05 05 08 Electrical Distribution Logic 2 05 05 09 Ground Service Bus 2 05 05 10 Avionics Master 2 05 05 11 AC System 2 05 05 12 EDL Configurations and Diagrams 2 05 10 01 Abnormal Operation Configurat...

Page 1701: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 00 Page 2 Code 01 MARCH 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1702: ...wer system is comprised of Four independent generators 28 V DC 400 A engine driven One APU starter generator 28 V DC 400 A Two Nickel Cadmium batteries 24 V DC 44 Ah 1 hour rate One lead acid backup b...

Page 1703: ...normal operation the electrical DC system is divided into isolated left and right electrical networks The left network includes generators 1 and 3 driven by engine 1 Operated in parallel generators 1...

Page 1704: ...TOR 4 GLC 4 APU STARTING CONTACTOR APU CONTACTOR LINE ALC ASC BUS TIE BTC 1 GROUND POWER CONTACTOR GPC BATTERY CONTACTOR 1 BC 1 BATTERY CONTACTOR 2 BC 2 SHED BUS CONTACTOR 1 SBC 1 SHED BUS CONTACTOR 2...

Page 1705: ...ing this overcurrent the GCU isolates the system networks opening the BTCs If any generator remains overloaded due to the failure it is then deenergized and disconnected from the bus As long as the ge...

Page 1706: ...tion above the GPU receptacle simultaneously illuminates When GPU AVAIL is illuminated and the batteries are not connected to the buses only the GROUND SERVICE BUS is supplied through the external pow...

Page 1707: ...c EDL When the GPU is connected the battery contactors open so that only the GPU can supply the load buses When on the ground with the batteries as the only electrical power source EDL deenergizes the...

Page 1708: ...RS The primary source of electrical power are the four 28 V DC 400 Amperes independent engine driven brushless generators two installed on each engine accessory gearbox Each generator is automatically...

Page 1709: ...perative the APU generator automatically replaces the inoperative generator Three electrical sources may be used to power an APU start ground power unit battery 2 or battery 2 assisted by the main gen...

Page 1710: ...ogic EDL differs depending on whether the airplane is on the ground or in flight In flight some buses are deenergized depending on the power source available On the ground all the DC buses are energiz...

Page 1711: ...C BC 1 and BC 2 are open The Ground Service Bus supplies electrical power for airplane servicing and maintenance while on the ground It functions independently of the Electrical Distribution Logic and...

Page 1712: ...t from the load buses This prevents undesirable voltage transients during APU starting on the ground The avionics master system consists of six buses Avionics Switched DC Buses 1A 1B 2A 2B and Avionic...

Page 1713: ...er Button is pressed the 115 V AC BUS is automatically energized If the DC Bus 1 is deenergized the inverter becomes inoperative To reduce pilot workload the AC Power Button should remain pressed even...

Page 1714: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 36 2 05 05 Page 13 Code 01 AOM 145 1114 AC GENERATION AND DISTRIBUTION SCHEMATICS If installed...

Page 1715: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 05 Page 14 Code 01 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 1716: ...Panel are the following Generator Buttons pressed GPU Button released Battery Selector Knobs set to AUTO position Essential Power Button released Bus Tie Selector Knob set to AUTO position Shed Buses...

Page 1717: ...available GLC 1 or 3 is open ALC is closed BTC 1 is closed and BTC 2 is open Loss of one right side generator network 2 Without APU generator available GLC 2 or 4 is open ALC is open BTC 2 is closed...

Page 1718: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL MARCH 28 2002 2 05 10 Page 3 Code 01 CONFIGURATION 1...

Page 1719: ...rators without APU generator available GLCs from affected generators are open ALC is open BTC 1 and BTC 2 are closed SBC 1 and SBC 2 are open NOTE Depending on the amount of load on the remaining buse...

Page 1720: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 22 2 05 10 Page 5 Code 01 CONFIGURATION 2...

Page 1721: ...R 1 and BBR 2 are open EIC EBC 1 EBC 2 and BC 2 are closed NOTE This operational mode is activated for in flight condition only A 1 second time delay is provided to avoid inadvertent switching to emer...

Page 1722: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL JUNE 28 2002 2 05 10 Page 6A Code 01 CONFIGURATION 3 Electrical Emergency Condition...

Page 1723: ...message on the EICAS EBC 1 EBC 2 EIC and BC 2 are closed BTC 1 BTC 2 and BC 1 are open GLCs from operating generators are closed SBC 1 and SBC 2 are closed if at least three generators are on NOTE BC...

Page 1724: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 23 2 05 10 Page 6C Code 01 CONFIGURATION 3A...

Page 1725: ...ls to close Case 1 Loss of all generators and BTC 1 is closed DC BUS 1 is energized ELEC ESS XFR FAIL warning message on the EICAS All GLCs and ALC are open BTC 2 BC 1 SBC 1 and SBC 2 are open EBC 1 E...

Page 1726: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 26 2 05 10 Page 7 Code 01 CONFIGURATION 3B...

Page 1727: ...oss of one associated generator and with APU generator Associated battery is removed from the affected DC bus through a fuse BTC 1 and BTC 2 are open Remaining GLC of the affected DC Bus opens isolati...

Page 1728: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL MARCH 28 2002 2 05 10 Page 9 Code 01 CONFIGURATION 4 Only EDL 1 Failure Shown...

Page 1729: ...oth Essential DC Buses energized and associated battery charged Both SBCs are open Short circuit at one DC Bus with loss of associated generators and without APU generator Both batteries are removed f...

Page 1730: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL MARCH 28 2002 2 05 10 Page 11 Code 01 CONFIGURATION 5 Only EDL 1 Failure Shown...

Page 1731: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 10 Page 12 Code 01 MARCH 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1732: ...ANUAL ELECTRICAL MARCH 28 2002 2 05 10 Page 13 Code 01 NORMAL ABNORMAL AND EMERGENCY OPERATION DIAGRAMS The following diagrams present the Electrical System layout when operating in normal abnormal an...

Page 1733: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 10 Page 14 Code 01 MARCH 28 2002 EDL STATUS DURING APU STARTING WITH BATTERIES...

Page 1734: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 22 2 05 10 Page 15 Code 01 EDL STATUS AFTER APU STARTING WITH BATTERIES...

Page 1735: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 10 Page 16 Code 01 REVISION 29 EDL STATUS DURING APU STARTING WITH GPU...

Page 1736: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 29 2 05 10 Page 17 Code 01 EDL STATUS AFTER APU STARTING WITH GPU...

Page 1737: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 10 Page 18 Code 01 REVISION 22 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1738: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL MARCH 28 2002 2 05 10 Page 19 Code 01 EDL STATUS DURING NORMAL OPERATION...

Page 1739: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 10 Page 20 Code 01 MARCH 28 2002 EDL STATUS AFTER LOSS OF GENERATOR 1 WITHOUT APU GENERATOR...

Page 1740: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 29 2 05 10 Page 21 Code 01 EDL STATUS AFTER LOSS OF GENERATOR 1 WITH APU GENERATOR...

Page 1741: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 10 Page 22 Code 01 REVISION 22 EDL STATUS AFTER LOSS OF GENERATORS 1 AND 3 WITHOUT APU GENERATOR...

Page 1742: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 22 2 05 10 Page 23 Code 01 EDL STATUS AFTER LOSS OF GENERATORS 1 AND 3 WITH APU GENERATOR...

Page 1743: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 10 Page 24 Code 01 REVISION 26 EDL STATUS DURING LOSS OF THREE ENGINE GENERATORS WITHOUT APU GENERATOR...

Page 1744: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 22 2 05 10 Page 25 Code 01 EDL STATUS AFTER LOSS OF ALL THE GENERATORS ELECTRICAL EMERGENCY CONDITION...

Page 1745: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 10 Page 26 Code 01 REVISION 29 EDL STATUS AFTER A SHORT CIRCUIT AT DC BUS 1 WITH ALL GENERATORS ON...

Page 1746: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 29 2 05 10 Page 27 Code 01 EDL STATUS AFTER A SHORT CIRCUIT AT DC BUS 1 WITH LOSS OF GENERATOR 1 AND WITHOUT APU GENERATOR...

Page 1747: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 10 Page 28 Code 01 REVISION 29 EDL STATUS AFTER A SHORT CIRCUIT AT DC BUS 1 WITH LOSS OF GENERATORS 1 2 AND 3 WITH APU GENERATOR ON...

Page 1748: ...APU generator current is above 400 A CAUTION APU GEN OFF BUS APU generator is disconnected from electrical network due to open ALC with APU RPM above 95 plus seven seconds This is caused by generator...

Page 1749: ...ARCH 28 2002 EICAS MESSAGES continued TYPE MESSAGE MEANING CAUTION ELEC EMERG ABNORM Improper transfer to electrical emergency condition has occurred 115 VAC BUS OFF 115 VAC bus is deenergized ADVISOR...

Page 1750: ...nal power is connected to the electrical network A striped bar illuminates inside the button when it is pressed 3 APU STARTER GENERATOR BUTTON Connects pressed or disconnects released the APU starter...

Page 1751: ...buses A striped bar illuminates inside the button when it is released 8 BACKUP BATTERY BUTTON Connects pressed or disconnects released the backup battery to from the electrical system A striped bar il...

Page 1752: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL MARCH 28 2002 2 05 15 Page 5 Code 01 ELECTRICAL SYSTEM PANEL...

Page 1753: ...white during normal operation Digits and boxes are amber when the generator is inadvertently off bus or when the current is higher than 400 A Ranges from 0 to 600 A with a resolution of 5 A NOTE The A...

Page 1754: ...battery is inadvertently off bus Ranges from 0 to 40 0 V with a resolution of 0 1 V TEMPERATURE Boxes are white during battery normal operation Boxes are amber when the battery is off bus Digits are g...

Page 1755: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 15 Page 8 Code 01 REVISION 22 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1756: ...AOM 145 1114 CIRCUIT BREAKER PANEL AND LOAD DISTRIBUTION CIRCUIT BREAKER PANEL The Circuit Breaker Panel is divided in areas associated to electrical system buses Columns and lines on the circuit brea...

Page 1757: ...ELECTRICAL AIRPLANE OPERATIONS MANUAL 2 05 20 Page 2 Code 01 REVISION 41 Copyright byEmbraer Refertocoverpagefordetails AOM 145 1114 CIRCUIT BREAKER PANEL TYPICAL...

Page 1758: ...AIRPLANE OPERATIONS MANUAL ELECTRICAL REVISION 41 2 05 20 Page 3 Code 01 Copyright byEmbraer Refertocoverpagefordetails AOM 145 1114 CIRCUIT BREAKER PANEL TYPICAL...

Page 1759: ...UMATIC HSV 1 PRESSURIZATION CONTROL SPEED BRAKE STATIC PORT HEATING 1 STROBE LIGHTS TAT 1 SENSOR HEATING TCAS 2000 VENTRAL FUEL TRANSFER PUMP A EMB 145 XR WINDSHIELD HEATING 1 WINDSHIELD WIPER SYSTEM...

Page 1760: ...ESSENTIAL BUS AHRS POWER 1 DATA ACQUISITION UNIT DISPLAY PRCS CONTROL POWER 1 EICAS POWER IRS POWER 1 BACKUP BUS 1 NONE Applicable only if DUAL FMS is installed AVIONIC SWITCHED DC BUS 2A AUTOPILOT 2...

Page 1761: ...AM AIR DISTRIBUTION RMU 1 POWER CONTROL RUDDER CONTROL SYSTEM 2 SPS SHAKER 1 CHANNEL 1 VHF SYSTEM 1 AVIONIC SWITCHED ESSENTIAL DC BUS 1 ADF 1 VOR ILS MB 1 ESSENTIAL DC BUS 2 AIR GND POSITION SYSTEM D...

Page 1762: ...rs 2 06 05 04 Passenger Cabin Lighting 2 06 10 01 Sterile Light Optional 2 06 10 02 Courtesy and Stairs Lighting 2 06 10 02 Controls and Indicators 2 06 10 03 External Lighting 2 06 15 01 Service Comp...

Page 1763: ...LIGHTING AIRPLANE OPERATIONS MANUAL 2 06 00 Page 2 Code 01 JANUARY 21 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1764: ...ights of fixed intensity commanded by a switch on the overhead panel One light is located above the pilot s seat and the other is located above the copilot s seat READING LIGHTS In order to provide ad...

Page 1765: ...der the glareshield panel two for the pilot s and central side and the other for the copilot s side Light intensity is controlled by potentiometer knobs located on each side of the glareshield panel a...

Page 1766: ...AIRPLANE OPERATIONS MANUAL LIGHTING JANUARY 21 2002 2 06 05 Page 3 Code 01 COCKPIT LIGHTING...

Page 1767: ...TROL KNOBS Regulate the brightness of associated chart holder lighting NOTE Chart light is turned on when the chart holder assembly is lifted 3 DISPLAYS LIGHTING CONTROL KNOBS Regulate the brightness...

Page 1768: ...AIRPLANE OPERATIONS MANUAL LIGHTING JANUARY 21 2002 2 06 05 Page 5 Code 01 GLARESHIELD PANEL...

Page 1769: ...nel overhead panel control pedestal and right lateral console will illuminate allowing verification of lamp integrity The fire handles APU fire extinguish button BAGG EXTG button electromechanical GUS...

Page 1770: ...AIRPLANE OPERATIONS MANUAL LIGHTING JANUARY 21 2002 2 06 05 Page 7 Code 01 OVERHEAD PANEL...

Page 1771: ...JANUARY 21 2002 FLIGHT CREW READING LIGHTS 1 INNER RING Provides turn on off and dimming control 2 OUTER RING Provides reading area adjustment allowing light beam orientation up to 35 degrees from the...

Page 1772: ...n the bright mode Two illuminated LAVATORY OCCUPIED signs indicate when the lavatory is in use A RETURN TO SEAT sign in the lavatory illuminates in conjunction with the FASTEN SEAT BELTS sign PASSENGE...

Page 1773: ...d on the main door ceiling panel above the entry area of the airplane to illuminate the stair entry area aisle toward cockpit and passenger cabin Service door light A light is installed on the service...

Page 1774: ...NTROLS AND INDICATORS ATTENDANT S PANEL 1 CABIN LIGHTING CONTROL BUTTONS ON All associated cabin lights are turned on OFF All associated cabin lights are turned off BRT All associated cabin lights are...

Page 1775: ...01 REVISION 38 AOM 145 1114 EM145AOM062022B DGN CABIN LTS CEILING SIDEWALL ON BRT DIM OFF ON BRT DIM OFF 1 ATTENDANT S CONTROL PANEL ATTENDANT S PANEL NOTE For airplanes Post Mod SB 145 33 040 the Dim...

Page 1776: ...shed when the main door is closed and lit when the main door is open NOTE The cockpit dome lights may be commanded through the Courtesy and Stairs Lighting Control Knob provided the airplane is deener...

Page 1777: ...LIGHTING AIRPLANE OPERATIONS MANUAL 2 06 10 Page 6 Code 01 REVISION 38 AOM 145 1114 EM145AOM062007A DGN 1 AUTO OFF COURTESY LTS ON COURTESY LIGHTING PANEL...

Page 1778: ...1114 OVERHEAD PANEL 1 FASTEN SEAT BELTS AND NO SMOKING SIGNS SWITCHES Turns on off the associated passenger signs 2 STERILE LIGHT SWITCH Turns on off the sterile light EM145AOM062019A DGN STERILE LIGH...

Page 1779: ...LIGHTING AIRPLANE OPERATIONS MANUAL 2 06 10 Page 8 Code 01 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 1780: ...lots during all taxi operation phases covering the runway and adjacent areas Two taxi lights are fitted on the nose landing gear strut and are commanded by a single switch located on the overhead pane...

Page 1781: ...rovided with only two white strobe lights which are located at the winglets Red beacon lights are mounted on the upper and lower fuselage Two different switches one for strobe lights and another for t...

Page 1782: ...AIRPLANE OPERATIONS MANUAL LIGHTING DECEMBER 20 2002 2 06 15 Page 3 Code 01 EXTERNAL LIGHTS EMB 135 140 145 EXCEPT EMB 145XR...

Page 1783: ...LIGHTING AIRPLANE OPERATIONS MANUAL 2 06 15 Page 4 Code 01 DECEMBER 20 2002 EXTERNAL LIGHTS EMB 145XR...

Page 1784: ...ts installed on the ceiling panel The baggage lights operate according to the following conditions They come on automatically whenever the cargo door is open and they go off when the door is closed Fo...

Page 1785: ...LIGHTS SWITCH Turns on off the logotype lights 3 TAXI LIGHTS SWITCH Turns on off the taxi lights NOTE Taxi lights are not turned on if nose landing gear is not down and locked regardless of the Taxi L...

Page 1786: ...AIRPLANE OPERATIONS MANUAL LIGHTING JANUARY 21 2002 2 06 15 Page 7 Code 01 OVERHEAD PANEL...

Page 1787: ...LIGHTING AIRPLANE OPERATIONS MANUAL 2 06 15 Page 8 Code 01 JANUARY 21 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1788: ...n of the external main door and service door areas when the door is open Internal emergency lights consist of the cockpit light aisle lights main door lights galley service door lights overwing emerge...

Page 1789: ...ght ambient conditions exist throughout flight or if cabin lighting is operated on the ON or BRIGHT settings Charge Bin door position Charge duration minutes Operational duration when lights are extin...

Page 1790: ...AIRPLANE OPERATIONS MANUAL LIGHTING JANUARY 21 2002 2 06 20 Page 3 Code 01 AREA ILLUMINATED BY EMERGENCY LIGHTING...

Page 1791: ...lied by the dedicated batteries ARM Emergency lights are in standby mode lights turned off and the batteries being charged and illuminate automatically in case of an electrical emergency with power su...

Page 1792: ...AIRPLANE OPERATIONS MANUAL LIGHTING JANUARY 21 2002 2 06 20 Page 5 Code 01 OVERHEAD PANEL...

Page 1793: ...DANT EMERGENCY LIGHTING CONTROL BUTTON NORM Emergency lights remain in the mode selected by Emergency Lighting Switch position in the cockpit ON Emergency lights are turned on with power supplied by d...

Page 1794: ...04 Controls and Indicators 2 07 10 07 EICAS Messages 2 07 10 10 Lavatory Fire Protection System 2 07 15 01 Lavatory Smoke Detection 2 07 15 01 Lavatory Fire Extinguishing 2 07 15 01 EICAS Message 2 0...

Page 1795: ...FIRE PROTECTION AIRPLANE OPERATIONS MANUAL 2 07 00 Page 2 Code 01 JANUARY 21 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1796: ...gage compartment is provided with a smoke detection system The class C baggage compartment is provided with a fire extinguishing system In addition the lavatory compartment is equipped with a dedicate...

Page 1797: ...FIRE PROTECTION AIRPLANE OPERATIONS MANUAL 2 07 05 Page 2 Code 01 JANUARY 21 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1798: ...tivates the warning system Localized fire or high intensity heating increases the central core s gas volume raising the sensor tube s internal pressure thus activating the alarm switch in the same man...

Page 1799: ...FIRE PROTECTION AIRPLANE OPERATIONS MANUAL 2 07 10 Page 2 Code 01 JANUARY 21 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1800: ...AIRPLANE OPERATIONS MANUAL FIRE PROTECTION JANUARY 21 2002 2 07 10 Page 3 Code 01 FIRE OVERHEAT DETECTION SCHEMATIC...

Page 1801: ...double check tee prevents the extinguishing agent of the remaining bottle from filling the emptied bottle in case of a second shot of the system The engine extinguisher bottles are discharged by pulli...

Page 1802: ...AIRPLANE OPERATIONS MANUAL FIRE PROTECTION JANUARY 21 2002 2 07 10 Page 5 Code 01 ENGINE AND APU FIRE EXTINGUISHING SYSTEM SCHEMATIC...

Page 1803: ...FIRE PROTECTION AIRPLANE OPERATIONS MANUAL 2 07 10 Page 6 Code 01 JANUARY 21 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1804: ...and discharges the APU fire extinguisher bottle On APU Model T 62T 40C11 a signal is sent to the ESU to simulate an overspeed condition in order to execute the APU shutdown procedure On APU Model T 6...

Page 1805: ...ated In this case repeat the test On airplanes equipped with class D baggage compartment the fire test is successfully completed if the conditions below occur simultaneously The following EICAS fire d...

Page 1806: ...AIRPLANE OPERATIONS MANUAL FIRE PROTECTION JANUARY 21 2002 2 07 10 Page 9 Code 01 ENGINE AND APU FIRE DETECTION EXTINGUISHING PANEL...

Page 1807: ...MEANING APU FIRE Fire in the APU WARNING ENG1 2 FIRE Fire in associated engine E1 2 FIREDET FAIL Associated engine fire detection system failed CAUTION APU FIREDET FAIL APU fire detection system fail...

Page 1808: ...from cigarettes The EMB 135 has an additional horn installed in the aft cabin section on the ceiling panel right in front of the lavatory door LAVATORY FIRE EXTINGUISHING A single fire extinguisher bo...

Page 1809: ...FIRE PROTECTION AIRPLANE OPERATIONS MANUAL 2 07 15 Page 2 Code 01 JANUARY 21 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1810: ...AIRPLANE OPERATIONS MANUAL FIRE PROTECTION JANUARY 21 2002 2 07 15 Page 3 Code 01 LAVATORY FIRE PROTECTION SYSTEM...

Page 1811: ...LIGHT red Flashes in case of smoke detection inside the lavatory In this case a horn is also activated 3 LAVATORY SMOKE DETECTOR TEST BUTTON guarded When pressed momentarily simulates a smoke detectio...

Page 1812: ...ctivate a red alarm flashing light and a horn In addition a warning message is presented on the EICAS The smoke sensor is less sensitive to smoke from cigarettes LAVATORY FIRE EXTINGUISHING A single f...

Page 1813: ...FIRE PROTECTION AIRPLANE OPERATIONS MANUAL 2 07 15 Page 2 Code 02 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 1814: ...LANE OPERATIONS MANUAL FIRE PROTECTION REVISION 39 2 07 15 Page 3 Code 02 AOM 145 1114 EXTINGUISHER FIRE BOTTLE WASTE COMPARTMENT LAVATORY SMOKE SENSOR EM145AOM000147A DGN LAVATORY FIRE PROTECTION SYS...

Page 1815: ...ion inside the lavatory In this case a horn is also activated 2 LAVATORY SMOKE DETECTOR HORN OFF BUTTON Turns off the horn alarm when pressed 3 LAVATORY SMOKE DETECTOR RESET BUTTON Cancels the horn an...

Page 1816: ...OPERATIONS MANUAL FIRE PROTECTION REVISION 39 2 07 15 Page 5 Code 02 AOM 145 1114 LAVATORY SMOKE DETECTION horn off reset test SIEMENS 4 FORWARD GALLEY 1 3 EM145AOM000146A DGN 2 LAVATORY SMOKE DETECT...

Page 1817: ...FIRE PROTECTION AIRPLANE OPERATIONS MANUAL 2 07 15 Page 6 Code 02 REVISION 39 AOM 145 1114 INTENTIONALLY BLANK...

Page 1818: ...is possible for airplanes equipped with an optional sight glass in the rear lavatory partition For some airplanes a switch is available to turn on the lights in the baggage compartment Refer to 2 06 1...

Page 1819: ...Code 01 REVISION 36 AOM 145 1114 EICAS MESSAGES TYPE MESSAGE MEANING WARNING BAGG SMOKE Smoke has been detected inside the baggage compartment CAUTION BAGG EXTBTL INOP Any of the bottles have been dis...

Page 1820: ...AIRPLANE OPERATIONS MANUAL FIRE PROTECTION REVISION 36 2 07 20 Page 3 Code 01 AOM 145 1114 BAGGAGE FIRE EXTINGUISHING SCHEMATIC...

Page 1821: ...tes that smoke was detected inside the baggage compartment or that the fan has been deactivated Button remains lit as long as there is smoke inside baggage compartment When pressed Discharges the bagg...

Page 1822: ...AIRPLANE OPERATIONS MANUAL FIRE PROTECTION REVISION 36 2 07 20 Page 5 Code 01 AOM 145 1114 BAGGAGE DETECTION EXTINGUISHING PANEL...

Page 1823: ...resets the system for operation 3 BAGGAGE SMOKE DETECTOR TEST SWITCH When pressed momentarily simulates a smoke detection condition and activates all associated alarms red alarm light and EICAS messag...

Page 1824: ...AIRPLANE OPERATIONS MANUAL FIRE PROTECTION REVISION 36 2 07 20 Page 7 Code 01 AOM 145 1114 BAGGAGE COMPARTMENT SMOKE DETECTOR...

Page 1825: ...FIRE PROTECTION AIRPLANE OPERATIONS MANUAL 2 07 20 Page 8 Code 01 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 1826: ...8 05 02 Engine and APU Fuel Distribution and Control 2 08 05 03 EICAS Messages 2 08 05 07 Controls and Indicators 2 08 05 08 Fuel System Panel 2 08 05 08 MFD Bezel 2 08 05 10 Fuel Page on MFD 2 08 05...

Page 1827: ...FUEL AIRPLANE OPERATIONS MANUAL 2 08 00 Page 2 Code 01 REVISION 17 INTENTIONALLY BLANK...

Page 1828: ...r each engine interconnected by a crossfeed line The fuel system ensure proper fuel supply to the engines and APU under all the operating conditions The system allows refueling and defueling operation...

Page 1829: ...2087 4173 2594 5187 Pounds 4600 2 9200 4 5717 4 11434 9 When performing pressure refueling the usable fuel quantity in each tank may be reduced by 7 9 US Gal STD ER and MP models or 13 2 US Gal LR mo...

Page 1830: ...eed operation Two PUMP PWR knobs energizes de energizes the electric pumps and the other two PUMP SEL knobs selects which pumps will be operating The remaining pumps will be on standby If the fuel pre...

Page 1831: ...el shutoff valve will close in the following conditions APU master knob positioned to OFF By pressing the APU fuel shutoff button By pressing the APU fire extinguishing button Automatically through th...

Page 1832: ...H ENGINE 1 FPMU DIRECT MEASURING STICK GRAVITY FILLER CAP EJECTOR PUMP DRAIN VALVE DUMP VALVE FLOAT VALVE FLAP VALVE LOW LEVEL SENSOR ELECTRICAL PUMP CHECK VALVE SHUTOFF VALVE MOTIVE FLOW FIRE HANDLE...

Page 1833: ...APU DIRECT MEASURING STICK GRAVITY FILLER CAP EJECTOR PUMP DRAIN VALVE DUMP VALVE FLOAT VALVE FLAP VALVE LOW LEVEL SENSOR ELECTRICAL PUMP CHECK VALVE SHUTOFF VALVE MOTIVE FLOW LEGENDS CHECK RELIEF VA...

Page 1834: ...IMBALANCE Fuel quantity in one tank differs by 363 kg 800 lb from the other tank Message is removed when difference between tanks decreases below 45 kg 100 lb CAUTION APU FUEL LO PRESS Fuel pressure...

Page 1835: ...e message will remain on continuously FUEL XFEED OPEN Crossfeed valve is open CONTROLS AND INDICATORS FUEL SYSTEM PANEL 1 CROSSFEED Selector Knob LOW1 Opens the crossfeed valve and turns off the selec...

Page 1836: ...114 FUEL ENG 1 ENG 2 APU OFF LOW LOW 1 2 XFEED PUMP SEL 1A 1C 2A 2C 2B 1B ON OFF PUMP PWR TANK 1 TANK 2 ON OFF FUEL ENG 1 ENG 2 APU OFF LOW LOW 1 2 XFEED PUMP SEL 1A 1C 2A 2C 2B 1B ON OFF PUMP PWR TAN...

Page 1837: ...L 1 FUEL SYSTEM and RESET BUTTON Pressing FUEL button selects the fuel system page on MFD Pressing the button a second time resets the fuel used to zero Fuel used must be reset individually on each MF...

Page 1838: ...AIRPLANE OPERATIONS MANUAL FUEL REVISION 39 2 08 05 Page 11 Code 01 AOM 145 1114 INTENTIONALLY BLANK...

Page 1839: ...er Amber dashes replace the indication in the event of any fault which affects fuel gauging 2 ANALOG FUEL QUANTITY INDICATION Quantity is indicated by a vertical bar and a pointer The colors and range...

Page 1840: ...L REVISION 39 2 08 05 Page 13 Code 01 AOM 145 1114 EM145AOM082005B DGN PUMP OFF TANK 2 PUMP FUEL TANK 1 A C MFD 131O KG 1 5 3 O RTN RNG T O A I ECS FUEL HYD ELEC M P RESET 1 2 4 TOTAL 17OO KG USED KG...

Page 1841: ...splayed continuously on EICAS Fuel quantity for each tank Green above 400 kg 880 lb Amber and boxed from 280 kg to 400 kg 620 lb to 880 lb Red and boxed below 280 kg 620 lb Fuel flow for each engine R...

Page 1842: ...l close stopping the refueling operation when The fuel level in the tanks lifts the associated pilot valve s float This level defines the maximum fuel volume approved for that tank through pressure re...

Page 1843: ...ueling shutoff valve allowing defueling operation To defuel the left tank the crossfeed knob on the overhead fuel panel in the cockpit must be positioned to LOW2 Complete gravity defueling may be achi...

Page 1844: ...ITY FILLER CAP DRAIN VALVE DUMP VALVE FLOAT VALVE FLAP VALVE PILOT VALVE VENT VALVE PRESSURE SWITCH REFUELING ADAPTER REFUELING LINE PILOT LINE ELECTRIC SIGNAL LEGENDS CHECK RELIEF VALVE DECRT TK SEL...

Page 1845: ...FUELING OPEN LIGHT WHITE Illuminates when the defueling shutoff valve is open 4 DEFUELING SWITCH GUARDED Actuates the defueling shutoff valve to open or to close 5 FUEL QUANTITY REMAINING INDICATOR Di...

Page 1846: ...d from the neutral position during refueling it interrupts the operation The refueling operation will be restored 4 seconds after switch return to the neutral position 8 FUEL QUANTITY SELECTED INDICAT...

Page 1847: ...OPEN CLOSED LH TANK RH TANK CLOSED CLOSED OPEN FUEL QTY REMAINING SELECTED 4 1 2 3 5 6 7 8 9 OR OPEN CLOSED THE TWO CLSD WHITE LIGHTS MUST BE ON BEFORE OPENING THE REFUEL SWITCH LH TANK CLSD STOP RFL...

Page 1848: ...easuring Stick can be found in the Ground Servicing Section 1 12 25 NOTE The EMB 145LR LU EMB 135LR ERJ 140 and EMB 145XR models have two additional measuring sticks one for each wing stub tank The ta...

Page 1849: ...FUEL AIRPLANE OPERATIONS MANUAL 2 08 15 Page 2 Code 01 REVISION 31 MEASURING STICK POINTS AIRPLANES WITHOUT WING STUB TANK...

Page 1850: ...AIRPLANE OPERATIONS MANUAL FUEL REVISION 31 2 08 15 Page 3 Code 01 MEASURING STICK POINTS AIRPLANES WITH WING STUB TANK...

Page 1851: ...FUEL AIRPLANE OPERATIONS MANUAL 2 08 15 Page 4 Code 01 REVISION 31 Pages 5 to 8 deleted INTENTIONALLY BLANK...

Page 1852: ...ge 1 Code 01 SECTION 2 09 AUXILIARY POWER UNIT TABLE OF CONTENTS Block Page General 2 09 05 01 Control System 2 09 05 04 APU Starting Operation 2 09 05 08 EICAS Messages 2 09 05 09 Controls and Indica...

Page 1853: ...AUXILIARY POWER UNIT AIRPLANE OPERATIONS MANUAL 2 09 00 Page 2 Code 01 JANUARY 21 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1854: ...Full Authority Digital Electronic Control FADEC Both control systems provide automatic full authority fuel scheduling from start to full load operation under all ambient conditions and operating modes...

Page 1855: ...d by a titanium firewall On the left side of the APU compartment an inspection door allows access and inspection of the APU s components The APU starter generator shaft drives an air cooling fan Air i...

Page 1856: ...AIRPLANE OPERATIONS MANUAL AUXILIARY POWER UNIT REVISION 37 2 09 05 Page 3 Code 01 AOM 145 1114 APU INSTALLATION...

Page 1857: ...US 1 The APU control system relays logic is supplied by ESS DC BUS 2 The APU shuts down immediately if the HOT BUS 1 is lost or shuts down after 6 seconds if the ESS DC BUS 2 is lost The fuel system i...

Page 1858: ...and an anti surge valve The flow limiting venturi maintains the bleed flow below a set value depending on air conditioning system requirements and atmospheric conditions thus maintaining the EGT withi...

Page 1859: ...AUXILIARY POWER UNIT AIRPLANE OPERATIONS MANUAL 2 09 05 Page 6 Code 01 REVISION 37 AOM 145 1114 APU MODEL T 62T 40C11 SCHEMATIC...

Page 1860: ...AIRPLANE OPERATIONS MANUAL AUXILIARY POWER UNIT REVISION 37 2 09 05 Page 7 Code 01 AOM 145 1114 APU MODEL T 62T 40C14 SCHEMATIC...

Page 1861: ...eed when the ESU commands starter disengagement and Start Fuel Solenoid Valve and ignition deenergization On the Model T 62T 40C14 APU at approximately 3 rotor speed on the ground or 0 in flight the F...

Page 1862: ...overspeed condition which aside shutting the APU down allows the ESU overspeed protection testing On APU Model T 62T 40C14 a stop request signal is sent to the FADEC in order to execute the APU shutdo...

Page 1863: ...below 5 and commands APU shutdown ON Energizes the ESU or FADEC commands the fuel shutoff valve to open enables indication and alarms on the EICAS and allows the APU to keep running after starting ST...

Page 1864: ...110 2 APU EGT INDICATION NORMAL OPERATION Ranges from 54 to 927qC Green from 54 to 680qC Amber and boxed from 681 to 717qC Red and boxed above 717qC START SEQUENCE Ranges from 54 to 927qC Green from 5...

Page 1865: ...AUXILIARY POWER UNIT AIRPLANE OPERATIONS MANUAL 2 09 05 Page 12 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 1866: ...Variable Geometry Actuation System 2 10 10 02 Fuel Nozzles 2 10 10 02 Lubrication System 2 10 15 01 Lubricating Oil Supply System 2 10 15 01 Oil Tank 2 10 15 01 Lube and Scavenge Pump 2 10 15 02 Oil...

Page 1867: ...ight Idle Thrust Schedule 2 10 40 05 Closed Loop Fan Speed Control 2 10 40 05 N1 N2 Overspeed Underspeed Protection 2 10 40 06 Interstage Turbine Temperature ITT Limiting 2 10 40 06 Acceleration Decel...

Page 1868: ...5 Takeoff Page on MFD 2 10 60 10 First Engine Backup Page on RMU 2 10 60 12 Thrust Reverser 2 10 70 01 General 2 10 70 01 Lock Protection 2 10 70 01 Operation 2 10 70 01 Operation Logic 2 10 70 02 EIC...

Page 1869: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 00 Page 4 Code 01 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 1870: ...flow turbofan engine The main design features include A single stage fan A 14 stage axial flow compressor with inlet guide vanes and five variable geometry stator stages A 2 stage high pressure turbi...

Page 1871: ...e available at the 9 th and 14 th stages compressor discharge A combustion liner assembly mixes air and fuel to support combustion and delivers a uniform high temperature gas flow to the turbine HIGH...

Page 1872: ...ssory gearbox is driven by the high pressure spool and provides driving pads for the following engine and airplane accessories Engine accessories Fuel Pump and Metering Unit FPMU Permanent Magnet Alte...

Page 1873: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 05 Page 4 Code 01 DECEMBER 20 2002 ROLLS ROYCE AE 3007 ENGINE...

Page 1874: ...nd flow rate for engine start correct engine operation engine stop and also controls the compressor variable geometry vanes The pump system contains a low pressure centrifugal pump and a high pressure...

Page 1875: ...passes oil flow to prevent fuel leaving the FCOC from being heated above 93 3 C 200 F The oil is also bypassed if the differential oil pressure is greater than 50 psi due to hung or cold starts After...

Page 1876: ...AIRPLANE OPERATIONS MANUAL POWERPLANT JUNE 28 2002 2 10 10 Page 3 Code 01 ENGINE FUEL SYSTEM SCHEMATIC...

Page 1877: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 10 Page 4 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1878: ...ressure at altitude A separate Tank Vent Valve protects the tank from over pressurization Oil to the accessory gearbox is distributed through cast passages to the various gear meshes and bearings Pres...

Page 1879: ...bypass valve opens and allows oil to bypass the filter during cold starts or when the filter becomes excessively contaminated A screen is located in the bypass inlet to prevent passage of particles T...

Page 1880: ...engine sumps and the accessory gearbox Each of the sump inlets to the pump includes a debris monitor with magnetic chip collector and screen in order to protect the pumping elements The gearbox sump i...

Page 1881: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 15 Page 4 Code 01 DECEMBER 20 2002 LUBRICATION SYSTEM SCHEMATIC...

Page 1882: ...s CABV The original type used two valves per engine located externally on the HP compressor at approximately the 12 00 and 6 00 O clock positions The second type is a single valve at 6 00 O clock posi...

Page 1883: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 20 Page 2 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1884: ...ower loss the ignition is turned on and the air vent valve is closed thus preventing fuel leakage through the vent port The PMA is the only source of power for the igniters If a PMA failure occurs the...

Page 1885: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 25 Page 2 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1886: ...ring start as soon as the PMA provides sufficient power The ignition is not automatically deactivated when the start cycle is completed If the engine is already running both FADECs activate their igni...

Page 1887: ...clutch and an output shaft The ATS converts pneumatic energy into driving torque for engine gas generator spool acceleration up to the self sustained speed during the starting cycle The air exhaust fr...

Page 1888: ...zes the engine 2 start relay When the engine gas generator attains 53 N2 a validation time of 10 seconds elapses before the message E2 ATS SOV OPN appears on the EICAS At 56 4 N2 the FADEC sends a sig...

Page 1889: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 30 Page 4 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 1890: ...AIRPLANE OPERATIONS MANUAL POWERPLANT REVISION 37 2 10 30 Page 5 Code 01 AOM 145 1114 PNEUMATIC STARTING SYSTEM SCHEMATIC...

Page 1891: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 30 Page 6 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 1892: ...om approximately 90 psi to the actual pressure value after the 2 minutes period is expired LOW OIL PRESSURE SENSOR The function of the low oil pressure sensor is to give an indication when oil pressur...

Page 1893: ...ITER SPARK RATE DETECTOR The engine igniter spark rate detectors are outputs from the ignition exciters that indicate that an electric field has collapsed in the exciter circuit A signal is available...

Page 1894: ...RITY DIGITAL ELECTRONIC CONTROL FADEC Each engine is controlled by one of two FADECs that are named FADEC A and FADEC B All signals between each FADEC and its respective engine and between the FADECs...

Page 1895: ...of which FADEC is used in flight For example If FADEC B was used for the last start when the pilot actuates the next start the selection logic will select FADEC A as shown in the following table Start...

Page 1896: ...AIRPLANE OPERATIONS MANUAL POWERPLANT REVISION 41 2 10 40 Page 3 Code 01 Copyright byEmbraer Refertocoverpagefordetails AOM 145 1114 FADEC SCHEMATIC...

Page 1897: ...keoff and actual A ICE system feedback in flight Takeoff mode N1REQUEST CALCULATION The N1REQUEST is a function of N1TARGET and Thrust Lever Angle The FADEC controls the engine to N1REQUEST at steady...

Page 1898: ...engine to Flight Idle Thrust which is scheduled in order to Avoid engine flameout overtemperature or inability to accelerate Provide the required bleed airflow pressure and temperature for the ECS an...

Page 1899: ...orates a high pressure rotor N2 underspeed shutdown This logic prevents damaging the turbine via an overtemperature condition if the engine attempts to operate at sub idle speed If N2 drops below 54 t...

Page 1900: ...em is capable of modulating thrust in response to thrust lever movement in the reversionary control mode However transient response times may be greater minimum thrust may exceed flight idle thrust an...

Page 1901: ...ever the FADEC in control is unable to safely control the engine it signals the alternate FADEC to automatically take over engine control MANUAL SELECTION The alternate FADEC may be manually selected...

Page 1902: ...ements of engine operating conditions The engine control system will not command a fuel flow that would result in exceeding rotor speed or temperature operating limits The engine control system is des...

Page 1903: ...Takeoff 1 Yes ALT T O 1 T O 1 Maximum Takeoff 1 Yes Yes T O 1 T O 1 Takeoff Yes Yes Yes T O T O RSV E Takeoff Yes E T O E T O RSV Takeoff Reserve Yes Yes Yes T O RSV E Takeoff Reserve Yes E T O RSV M...

Page 1904: ...e available engine thrust at the existing ambient conditions The following thrust modes are available ALTERNATE TAKEOFF ALT T O 1 All engines This mode is the normal all engines operating takeoff mode...

Page 1905: ...le takeoff mode A1E engine This is the One Engine Inoperative OEI mode for the normal all engines operating ALT T O 1 mode The FADECs will select T O 1 mode if the T O switch is pressed and the curren...

Page 1906: ...he FADECs on both engines This mode is also selected when the T O button is pushed and the pressure altitude is greater than 1700 ft above takeoff altitude The FADECs will select E T O mode if the T O...

Page 1907: ...n while in T O and the airplane is in post takeoff condition or on the ground NOTE The use of this mode requires a notation in the airplane maintenance log EXTENDED TAKEOFF RESERVE E T O RSV A1E engin...

Page 1908: ...r down and locked signal and there is no OEI signal or when pressure altitude is greater than 1700 ft above takeoff altitude and there is no OEI signal The CLB mode switch inputs to the FADECs are inh...

Page 1909: ...gher than 45 NOTE ATTCS capable is defined as E T O A1E engine T O A1P A1 3 or A1E engines or ALT T O 1 all engines mode selected with the airplane on ground and the engine running ATTCS TRIGGERING CO...

Page 1910: ...ARMING CONDITIONS The ATTCS disarms if any of the following conditions is met After being armed the Thrust Lever Angle is reduced below 42 ATTCS is triggered on either engine No ATTCS capable takeoff...

Page 1911: ...e Post takeoff phase ALT T O 1 T O 1 E T O T O T O RSV E T O E T O E T O RSV E T O CON CLB E CLB CRZ E T O T O 1 1 T O 1 E T O T O RSV 1 T O RSV E T O RSV E T O RSV 1 E T O RSV E T O RSV 1 If the ATTC...

Page 1912: ...pressed thrust will decrease to E T O FAN SPEED SCHEDULING The thrust management logic calculates the corrected fan speed request at any point in the flight envelope The scheduled corrected fan speed...

Page 1913: ...mode The Target Thrust N1 Target is defined as the thrust corresponding to the corrected fan speed scheduled with the thrust lever at the THRUST SET position A target thrust is computed for each thrus...

Page 1914: ...s Any movement of the thrust levers above the THRUST SET position results in the scheduling of the maximum takeoff thrust regardless of the current thrust mode except for A1E engines refer to A1E Thru...

Page 1915: ...Condition REF A ICE which is the anti ice system condition ON OFF that the FADEC will consider to calculate N1TARGET This function is enabled during ground operations only and with thrust lever angle...

Page 1916: ...d the REF TO TEMP is within limits T2SYN 10 C The FADECs accept the takeoff data and successfully terminate the procedure The MFD displays the takeoff data The FADEC begins to calculate and display th...

Page 1917: ...he FADEC in control will be used The FADEC activates the ignition system when N2 is at approximately 14 and commands the fuel solenoid valve to open when N2 is at approximately 31 5 28 5 for airplanes...

Page 1918: ...the reference value the FADEC shuts the engine down Therefore if the temperature exceedance is higher the command to shut the engine down will be shorter in time The FADEC also reduces the fuel flow t...

Page 1919: ...the engine fuel solenoid valve to close The normal sequence only occurs with the thrust levers positioned at Idle Thrust levers should be positioned at IDLE before the Start Stop Knob is positioned at...

Page 1920: ...1 2 OIL LOW PRESS Oil pressure has dropped below 34 psi and the engine is running or the pressure switch has failed at the closed position and the engine is not running WARNING E1 2 LOW N1 Engine does...

Page 1921: ...O DISP if applicable There are different FADEC applications installed in the airplane ENG 1 2 OUT if applicable N2 has dropped below 8500 rpm underspeed shutdown limit uncommanded E1 2 NO DISP if appl...

Page 1922: ...ature source E1 2 FADEC FAULT if applicable A dispatchable MMEL FADEC fault was detected E1 2 CTL A B DEGRAD if applicable A dispatchable MMEL FADEC fault was detected E1 2 SHORT DISP if applicable A...

Page 1923: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 50 Page 22 Code 01 REVISION 41 Copyright byEmbraer Refertocoverpagefordetails AOM 145 1114 INTENTIONALLY BLANK...

Page 1924: ...ovides ground and flight idle thrust settings MAX REV Provides maximum reverse thrust NOTE Protection against inadvertent thrust reverser command in flight is provided through the mechanical idle stop...

Page 1925: ...5AOM102008A DGN MAX THRUST SET IDLE FREE FREE LOCKED MAX REV MAX REV GUST LOCK GO AROUND GO AROUND F R I CTIO N L O C K THRUST RATING CON CLB CRZ CONTROL PEDESTAL 1 2 3 4 STOP 85 MAX THRUST SET REVERS...

Page 1926: ...e fourth pressing if REF TO TEMP is within limits the takeoff data is accepted and the procedure is successfully accomplished For complete procedures refer to Takeoff Data Setting paragraph NOTE The b...

Page 1927: ...y position that initiates the engine start cycle NOTE On airplanes Post Mod SB 145 71 0003 or S N 145 075 and on each Start Stop selector knob is equipped with a transparent protection guard over the...

Page 1928: ...th a resolution of 0 1 Indicated by a cyan T shaped bug Indication is removed from the display for request values greater than 100 or less than 0 2 THRUST RATING MODE ANNUNCIATION Indicates the curren...

Page 1929: ...IN CONTROL ANNUNCIATION Indicates the FADEC channel that is controlling the engine Labels A or B Color green 6 IGNITION CHANNEL ANNUNCIATION Indicates the ignition channel that is enabled Labels IGN...

Page 1930: ...nds to the color of the scale 8 N2 INDICATION Displays N2 in RPM percentage Digits Ranges from 0 to 120 RPM with a resolution of 0 1 Colors EICAS 18 5 and before green from 0 to 102 4 red from 102 5 a...

Page 1931: ...ted by a green filled triangle Ranges from 0 to 100 RPM Indication is removed from the display for request values greater than 100 or less than 0 13 OIL PRESSURE INDICATION Scale pointer and digit col...

Page 1932: ...4 EM145AOM102010A DGN 1 2 3 4 5 6 7 8 9 10 11 13 12 EICAS N1 ITT N2 PPH FF PPH LB FQ LB OIL VIB TEMP LP HP PRESS 79 79 1OO 1OO 9OO 99O 99 9 99 9 99O 1OOO 55O 55O 75 O 75 O A IGN AB AB IGN A REV REV 88...

Page 1933: ...ates reference takeoff temperature as adjusted through the takeoff data set control In flight the indication is removed from the display 3 REFERENCE ANTI ICE STATUS INDICATION Indicates reference anti...

Page 1934: ...NE OPERATIONS MANUAL POWERPLANT REVISION 39 2 10 60 Page 11 Code 01 AOM 145 1114 EM145AOM102011A DGN 1 REF A ICE OFF ENGINE 4 QT 1 QT OIL LVL MFD 2 3 4 T O MODE T O 1 O REF TO TEMP 25 C TAKEOFF PAGE O...

Page 1935: ...Only the N1 indication contains analog and digital indication The other indications are in digital format Label and legend color white Data color limits same as the EICAS display EM145AOM102012A DGN T...

Page 1936: ...events the door from deploying In the stowed position the doors are held by the primary lock only with the secondary and tertiary locks remaining unloaded The primary and secondary locks are electrica...

Page 1937: ...ommands reverse thrust only after the Thrust Reverser doors both engines are completely deployed If the Thrust Lever is requesting forward thrust the FADEC will command IDLE thrust if the associated e...

Page 1938: ...and on the position of the engine thrust lever and reduces the engine thrust to IDLE if there is an indication of an inadvertent thrust reverser deployment in flight which normally is not possible du...

Page 1939: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 70 Page 4 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1940: ...AIRPLANE OPERATIONS MANUAL POWERPLANT JUNE 28 2002 2 10 70 Page 5 Code 01 THRUST REVERSER...

Page 1941: ...POWERPLANT AIRPLANE OPERATIONS MANUAL 2 10 70 Page 6 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1942: ...MANUAL HYDRAULIC JANUARY 21 2002 2 11 00 Page 1 Code 01 SECTION 2 11 HYDRAULIC TABLE OF CONTENTS Block Page General 2 11 05 01 System Description 2 11 05 02 EICAS Messages 2 11 05 05 Controls and Ind...

Page 1943: ...HYDRAULIC AIRPLANE OPERATIONS MANUAL 2 11 00 Page 2 Code 01 JANUARY 21 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1944: ...There are ground connections for refilling and ground tests purposes Indications of hydraulic system parameters are provided on the MFD and EICAS displays The services provided by each hydraulic syst...

Page 1945: ...hydraulic fluid overheat This valve may be closed either through the engine fire extinguishing handle or through a dedicated button on the overhead panel ENGINE DRIVEN PUMP The engine driven pump pro...

Page 1946: ...AIRPLANE OPERATIONS MANUAL HYDRAULIC JANUARY 21 2002 2 11 05 Page 3 Code 01 HYDRAULIC SYSTEM SCHEMATIC...

Page 1947: ...filtered and returned to the reservoir The manifold incorporates two pressure switches to detect low hydraulic pressure and a pressure transducer to indicate system pressure Signals from the pressure...

Page 1948: ...YS 1 2 OVHT Associated hydraulic system fluid temperature is above 90 C E1 2 HYD PUMP FAIL Engine driven pump is not generating pressure with associated engine running E1 2 HYDSOV CLSD Associated hydr...

Page 1949: ...the associated engine pump shutoff valve A striped bar illuminates in the button to indicate that it is pressed 2 ELECTRIC HYDRAULIC PUMP CONTROL KNOB OFF Associated pump is turned off AUTO Associate...

Page 1950: ...AIRPLANE OPERATIONS MANUAL HYDRAULIC JANUARY 21 2002 2 11 05 Page 7 Code 01 HYDRAULIC SYSTEM PANEL...

Page 1951: ...er green when greater than 1 liter amber when equal to or less than 1 liter Pointer disappears if data is invalid 2 PRESSURE INDICATION Ranges from 0 to 4000 psi with a resolution of 100 psi Digits gr...

Page 1952: ...Gear Extension 2 12 05 05 Landing Gear Warning 2 12 05 06 EICAS Messages 2 12 05 07 Controls and Indicators 2 12 05 07 Brake System 2 12 10 01 Normal Brake System 2 12 10 02 Emergency Parking Brake S...

Page 1953: ...LANDING GEAR AND BRAKES AIRPLANE OPERATIONS MANUAL 2 12 00 Page 2 Code 01 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 1954: ...king and steering capabilities The extension retraction steering and braking functions are hydraulically assisted electronically controlled and electronically monitored EICAS indications and messages...

Page 1955: ...various equipment operations Logic processing includes the position signal and its validity If all proximity switch signals are valid four signals are processed to assure that at least three signals...

Page 1956: ...RETRACTION Landing gear retraction is commanded through the Landing Gear Lever installed on the main panel Positioning the lever to the UP position signals the LGEU to command the Nose Gear Door Sole...

Page 1957: ...FREE FALL LEVER AT NORMAL POSITION AND LANDING GEAR NOTE LEVER IN DOWN POSITION DOORS CLOSE LINE DOORS OPEN NOSE GEAR DOORS SOLENOID VALVE UP UNLOCK ACTUATOR ACTUATOR UNLOCK DOWN NOSE GEAR TO RIGHT LA...

Page 1958: ...ould there occur a normal landing gear extension failure This system bypasses the LGEU and actuates directly the Landing Gear Electrovalve and the Nose Gear Doors Solenoid Valve The control switch is...

Page 1959: ...WARNING A LANDING GEAR voice message is provided to alert pilots any time the airplane is in a landing configuration and the gear legs are not locked down The warning may be activated under one of thr...

Page 1960: ...h air ground system indication CAUTION NLG UP DOOR OPN if applicable Nose LG is locked up and nose LG door is open NOTE 1 If the message is displayed for about 3 or 5 seconds during the landing gear e...

Page 1961: ...LANDING GEAR AND BRAKES AIRPLANE OPERATIONS MANUAL 2 12 05 Page 8 Code 01 REVISION 38 AOM 145 1114 EM145AOM122002A DGN 1 MAIN PANEL 2 UP DN REL LOCK DN LANDING GEAR CONTROL BOX...

Page 1962: ...e actuated position by a mechanical lock 2 FREE FALL LEVER UNLOCK BUTTON When pressed unlocks the free fall lever allowing it to be returned to the normal position thus restoring the hydraulic operati...

Page 1963: ...LANDING GEAR AND BRAKES AIRPLANE OPERATIONS MANUAL 2 12 05 Page 10 Code 01 REVISION 38 AOM 145 1114 EM145AOM122003A DGN 2 1 COCKPIT FLOOR NORMAL DOORS 3 GEAR DOORS FREE FALL LEVER COMPARTMENT...

Page 1964: ...inoperative with Flap Selector Lever set lower than 22 one thrust lever set below 59 and the other thrust lever set below 45 or the associated engine inoperative An amber indication bar illuminates i...

Page 1965: ...PERATIONS MANUAL 2 12 05 Page 12 Code 01 REVISION 38 AOM 145 1114 EM145AOM122004A DGN CONTROL PEDESTAL LG WRN CUTOUT THE LANDING GEAR WARNING CUTOUT BUTTON MAY ALSO BE LOCATED ON THE MAIN PANEL NOTE L...

Page 1966: ...1 AOM 145 1114 GLARESHIELD PANEL 1 NOSE LANDING GEAR DOORS INDICATION LIGHT IF INSTALLED Illuminates to indicate that the nose landing gear is locked in the retracted position and at least one door is...

Page 1967: ...een box Landing gear in transit is indicated when the box is cross hatched in amber and black Landing gear up and locked is indicated by a white UP label inside a white box Landing gear lever disagree...

Page 1968: ...5AOM122006A DGN LDG GEAR UP UP UP LDG GEAR DN DN LEFT NOSE RIGHT LDG GEAR UP UP UP LDG GEAR UP UP LDG GEAR DN DN LDG GEAR UP UP DN DN 1 1 LANDING GEAR DOWN AND LOCKED 2 LANDING GEAR UP AND LOCKED 3 LA...

Page 1969: ...SPLRS TEMP LP HP PRESS CAB ALT CAB P CAB RATE APU FT PSI FPM C ROLL PITCH YAW 9 UP 100 600 2000 7 5 7000 79 79 100 100 900 990 99 9 99 9 990 1000 550 550 75 0 75 0 A IGN AB AB IGN A REV REV 88 1 MAX T...

Page 1970: ...ency parking brake system is supplied only by hydraulic system 2 and is mechanically actuated Normal braking is controlled by the pedals Emergency braking is controlled by the emergency parking brake...

Page 1971: ...raulic system 2 and the ESS DC BUS 2 supply the main brake system for the control of the inboard wheels Pressure and wheel speed transducers send signals to the BCU so that it can monitor brake perfor...

Page 1972: ...UNIT LIGHT EMERGENCY PARKING BRAKE HANDLE HYDRAULIC SYSTEM 2 RETURN SUPPLY RELIEF VALVE HYDRAULIC SYSTEM 2 RETURN EMERGENCY PARKING BRAKE VALVE PRESSURE SWITCH WHEEL SPEED TRANSDUCER PRESSURE TRANSDUC...

Page 1973: ...eels a skidding is probably occurring and braking pressure has to be relieved After that wheel speed has returned to the average speed normal braking operation is restored The anti skid does not apply...

Page 1974: ...PREVENTS THE WHEELS FROM SKIDDING IF ONE OF THE WHEELS LOCKS THE ANTI SKID FUNCTION REDUCES THE BRAKE PRESSURE OF THE ASSOCIATED PAIR THUS ELIMINATING THE SKIDING IF THE PILOT APPLIES DIFFERENTIAL PED...

Page 1975: ...r proximity switch fails at the air position the brake system will operate normally However if both proximity switches fail at the air position braking capacity will be available only for wheel speeds...

Page 1976: ...AIRPLANE OPERATIONS MANUAL LANDING GEAR AND BRAKES REVISION 40 2 12 10 Page 7 Code 01 AOM 145 1114 INTENTIONALLY BLANK...

Page 1977: ...s proportional to the handle displacement A BRAKE ON indicating light illuminates to indicate that pressure is being applied to the wheel brakes A locking device allows the handle to be held in the ac...

Page 1978: ...AIRPLANE OPERATIONS MANUAL LANDING GEAR AND BRAKES REVISION 40 2 12 10 Page 9 Code 01 AOM 145 1114 EMERGENCY PARKING BRAKE SYSTEM SCHEMATIC...

Page 1979: ...perative CAUTION BRAKE OVERHEAT Any brake temperature has exceeded 420 C BRAKE DEGRADED Total or partial loss of braking capability of one outboard wheel 1 or 4 and or one inboard wheel 2 or 3 or inte...

Page 1980: ...AOM 145 1114 CONTROL PEDESTAL 1 EMERGENCY PARKING BRAKE HANDLE Actuates the emergency parking brake valve Pull the handle and rotate to lock in the fully actuated position EM145AOM122009A DGN P U L L...

Page 1981: ...nges from 0 to 500 C The scale and pointer are green when temperature is below 200 C and amber when equal or greater than 200 C The temperature indication pointer is removed from the display in case o...

Page 1982: ...tion For monitoring purpose a feedback potentiometer in the nose landing gear leg transmits nose wheel displacement information to the Electronic Control Module Maximum nose wheel displacement values...

Page 1983: ...ed to present a caution message In these cases for airplanes Post Mod SB 145 32 0104 or with an equivalent modification factory incorporated the tiller commands will be inhibited if wheel speed is abo...

Page 1984: ...EL POTENTIOMETER AIR GROUND GEAR POSITION STEERING HANDWHEEL PILOT S CONSOLE RUDDER PEDAL POTENTIOMETER ELECTRONIC CONTROL MODULE HYDRAULIC SYSTEM 1 RETURN EICAS POTENTIOMETER NOSE LANDING GEAR TOP VI...

Page 1985: ...4 Code 01 REVISION 40 AOM 145 1114 CONTROLS AND INDICATORS STEERING DISENGAGEMENT SWITCH GUARDED ENGAGED Allows normal steering system operation DISENGAGED Disables steering system operation EM145AOM1...

Page 1986: ...command or to reset the steering system after disconnection Rotate left or right step 2 with the steering handle on down position to command steering NOTE For airplanes operating under FAA certificati...

Page 1987: ...AL 2 12 15 Page 6 Code 01 REVISION 40 AOM 145 1114 CONTROL WHEEL 1 STEERING DISENGAGE BUTTON When pressed disengages the nose wheel steering system EM145AOM122014A DGN 1 NOTE PILOT S CONTROL WHEEL SHO...

Page 1988: ...19 79 m 64 ft 11 in 19 48 m 63 ft 11 in 17 10 m 56 ft 1 in 17 01 m 55 ft 9 in 18 19 m 59 ft 8 in 17 86 m 58 ft 7 in 15 21 m 49 ft 11 in 15 11 m 49 ft 7 in 13 08 m 42 ft 3 in 12 50 m 41 ft 0 in 6 39 m...

Page 1989: ...LANDING GEAR AND BRAKES AIRPLANE OPERATIONS MANUAL 2 12 15 Page 8 Code 01 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 1990: ...ADII EM145AOM122016 DGN R1 R6 R3 R4 R2 R5 76 3 10 m 60 ft 10 in 18 54 m RUN WAY MINIMUM WIDTH NOSE R1 NOSE GEAR R2 OUTBOARD GEAR R3 INBOARD GEAR R4 RIGHT WINGTIP R5 RIGHT TAILTIP R6 76 STEERING STEEL...

Page 1991: ...LANDING GEAR AND BRAKES AIRPLANE OPERATIONS MANUAL 2 12 15 Page 10 Code 01 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 1992: ...1A DGN R3 R5 R4 R 1 13 94 m 5 45 m 45ft 9 in R 17 ft 11 in R 65ft 8in 20 000 m R 2 R 6 13 53 44ft 4in 76 RUNWAY MINIMUM WIDTH NOSE R1 NOSE GEAR R2 OUTBOARD GEAR R3 INBOARD GEAR R4 RIGHT WINGTIP R5 RIG...

Page 1993: ...LANDING GEAR AND BRAKES AIRPLANE OPERATIONS MANUAL 2 12 15 Page 12 Code 01 REVISION 40 AOM 145 1114 INTENTIONALLY BLANK...

Page 1994: ...System Components 2 13 10 05 Horizontal Stabilizer Control Unit HSCU 2 13 10 05 Horizontal Stabilizer Actuator HSA 2 13 10 05 System Operation 2 13 10 06 Pitch Trim Channels Priority 2 13 10 08 Pitch...

Page 1995: ...20 08 Controls and Indicators 2 13 20 09 Flight Controls Panel 2 13 20 09 Control Pedestal Aft Panel 2 13 20 10 Main Panel 2 13 20 11 EICAS Indications 2 13 20 12 Gust Lock System 2 13 25 01 Mechanica...

Page 1996: ...ded in all axis Tabs are provided for pitch control only and are not available for ailerons and rudder A gust lock system blocks elevator controls on the ground avoiding damage to the control systems...

Page 1997: ...FLIGHT CONTROLS AIRPLANE OPERATIONS MANUAL 2 13 05 Page 2 Code 01 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 1998: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS JUNE 29 2001 2 13 05 Page 3 Code 01 FLIGHT CONTROL SURFACES...

Page 1999: ...FLIGHT CONTROLS AIRPLANE OPERATIONS MANUAL 2 13 05 Page 4 Code 01 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2000: ...Code 01 AOM 145 1114 PITCH CONTROL GENERAL Pitch control is provided by mechanically actuated elevators and an electrically positioned horizontal stabilizer which is commanded through the Pitch Trim...

Page 2001: ...r light illuminates on the control stand Controls cannot be reconnected during flight requiring maintenance action JAMMED ELEVATOR OPERATION The autopilot elevator servo and the stick pusher servo are...

Page 2002: ...pring tab to move in the opposite direction thus reducing the amount of force required to move the elevator Spring tab deflection is proportional to the control column force and therefore to the aerod...

Page 2003: ...ON HANDLE CONTROL PEDESTAL DISCONNECTION DEVICE AUTOPILOT SERVO STICK PUSHER SERVO ELEVATOR CAUTION LIGHT TO LEFT ELEVATOR ONLY RIGHT ELEVATOR SHOWN SERVO TAB SPRING TAB PITCH TRIM MARKS ELEVATOR SCHE...

Page 2004: ...These channel operations are totally independent from each other If the pitch trim main channel is inoperative the horizontal stabilizer can still be commanded through the backup channel The HSCU con...

Page 2005: ...the control pedestal aft panel and automatically commanded through the autopilot or speed brake actuation When using the main control wheel trim switches or the backup trim switch it is necessary to...

Page 2006: ...A 2 HORIZONTAL STAB POS CHANNEL FAILURE MAIN CHANNEL CHANNEL CUT OUT RELAY CUT OUT RELAY IC 600 1 ADC 1 ADC 2 AWU CMC IC 600 1 DAU 2 ADC 1 ADC 2 AWU CMC IC 600 1 DAU 2 M1 M2 ACTUATOR MAIN BACKUP MOTOR...

Page 2007: ...secondly commanded channel will become inoperative for the remainder of the flight and the respective message PIT TRIM 1 2 INOP will be displayed on EICAS PITCH TRIM SYSTEM PROTECTION Switch Protectio...

Page 2008: ...zontal stabilizer may stall the HSA inducing a temporary loss of pitch trim command For airplanes equipped with an HSCU P N 362100 1007 if the trim switches are actuated for a period of time that tota...

Page 2009: ...7 5 only This message will disappear after the button is released or Pitch trim system 1 main or system 2 backup being actuated with the HSA stalled WARNING PTRIM MAIN INOP Pitch trim main system is i...

Page 2010: ...s This message will disappear after the button is released or Backup trim switch actuation associated with horizontal stabilizer being commanded by the main channel or Backup trim switch being actuate...

Page 2011: ...1114 CONTROLS AND INDICATORS CONTROL STAND 1 ELEVATOR DISCONNECTION HANDLE When pulled disconnects pilot s from copilot s controls To pull the handle the safety lock button must be pressed 2 ELEVATOR...

Page 2012: ...FLIGHT CONTROLS REVISION 38 2 13 10 Page 13 Code 01 AOM 145 1114 EM145AOM132036A DGN CONTROL PEDESTAL ELEV DISC AIL DISC PRESS AND PULL CLOSE OPEN SPEED BRAKE GUST LOCK FREE FREE LOCKED LOCKED 1 PRES...

Page 2013: ...osition UP OFF DN rocker switch Operating the switch while the autopilot is engaged causes the autopilot to disengage It is divided into two segments which have to be actuated together to provide comm...

Page 2014: ...able 2 PITCH TRIM BACKUP SYSTEM CUTOUT BUTTON SAFETY GUARDED Cuts out pushed out or enables pushed in the Backup Pitch Trim system A striped bar illuminates inside the button to indicate that it is pu...

Page 2015: ...0 Page 16 Code 01 REVISION 38 AOM 145 1114 CONTROL PEDESTAL PITCH TRIM PITCH TRIM MAIN SYS BACKUP SYS CUTOUT CUTOUT ROLL TRIM YAW TRIM LWD RWD LEFT RIGHT BACKUP DN UP UP O 9 9 8 18 2 22 45 45 DOWN 3 1...

Page 2016: ...face position For the unit 8 displayed on the EICAS the surface position can be between 7 7q and 8 7q going upward and between 8 3q and 7 3q going downward The color change would occur when the surfac...

Page 2017: ...on the ground any thrust lever angle is above 60 and pitch trim is outside the green band the digits box and pointer turn red the aural warning TAKEOFF TRIM sounds and the EICAS warning message NO TA...

Page 2018: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS JUNE 29 2001 2 13 15 Page 1 Code 01 ROLL CONTROL Roll control is provided by hydraulically actuated ailerons controlled by either control wheel...

Page 2019: ...ly positions the ailerons In case of jamming of either aileron both panels may be disconnected through a handle located on the control pedestal This procedure will release the free aileron from its ja...

Page 2020: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS JUNE 29 2001 2 13 15 Page 3 Code 01 AILERON SCHEMATIC...

Page 2021: ...ed aileron neutral point A continuous command of the roll trim switch is limited to 3 seconds even if the trim switch is pressed longer than 3 seconds As a result when manually actuating the trim it i...

Page 2022: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS JUNE 29 2001 2 13 15 Page 5 Code 01 ROLL TRIM SCHEMATIC...

Page 2023: ...Aileron actuation through hydraulic power is inope rative CONTROLS AND INDICATORS FLIGHT CONTROLS PANEL 1 AILERON SHUTOFF BUTTON Enables pressed or disables released the supply of hydraulic power fro...

Page 2024: ...ND 1 AILERON DISCONNECTION HANDLE When pulled disconnects pilot s from copilot s controls To pull the handle the safety lock button must be pressed 2 AILERON DISCONNECTION LIGHT When the striped bar i...

Page 2025: ...NE OPERATIONS MANUAL 2 13 15 Page 8 Code 01 JUNE 29 2001 CONTROL PEDESTAL AFT PANEL 1 ROLL TRIM SWITCH spring loaded to neutral Pressed left or right actuates the roll trim to roll left or right CONTR...

Page 2026: ...2001 2 13 15 Page 9 Code 01 EICAS INDICATIONS 1 ROLL TRIM POSITION Indicated by a green pointer moving on a white semicircle scale Center of the scale is zero trimming Each mark represents 50 of trim...

Page 2027: ...FLIGHT CONTROLS AIRPLANE OPERATIONS MANUAL 2 13 15 Page 10 Code 01 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2028: ...ROLS REVISION 18 2 13 20 Page 1 Code 01 YAW CONTROL Yaw control is provided through hydraulically powered rudders which may also be mechanically commanded A yaw trim system assists in moving and holdi...

Page 2029: ...ivided into Rudder System 1 and Rudder System 2 The PCU also incorporates an artificial feel device that provides the pedals with an artificial feel of the aerodynamic load imposed on the rudder Rudde...

Page 2030: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS REVISION 19 2 13 20 Page 3 Code 01 RUDDER SCHEMATIC...

Page 2031: ...feature was designed to activate in case of a runaway rudder and a caution message is presented on the EICAS The rudder systems are automatically shut off if all conditions below are met simultaneousl...

Page 2032: ...is feature is applicable in the case of a runaway rudder and a caution message is presented on the EICAS The rudder systems are automatically shut off if all conditions below are met simultaneously Ru...

Page 2033: ...rudder deflection versions Airplanes with rudder main control primary stops located on the rear torque tube assembly that limit the ruder deflection at 10 on ground or in flight and Airplanes Post Mod...

Page 2034: ...ds even if the trim knob is actuated longer than 3 seconds As a result when manually actuating the trim it is necessary to release the knob after a 3 second actuation then actuate it again to continue...

Page 2035: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS JUNE 29 2001 2 13 20 Page 7 Code 01 YAW TRIM SCHEMATIC...

Page 2036: ...p erative RUDDER SYS 1 2 INOP Both Rudder Systems are inoperative CAUTION RUDDER OVERBOOST Both rudder systems hydraulic actuators are pressurized above 135 KIAS RUD HDOV PROTFAIL Disagreement between...

Page 2037: ...20 Page 9 Code 01 CONTROLS AND INDICATORS FLIGHT CONTROLS PANEL 1 RUDDER SHUTOFF BUTTON Enables pressed or disables released the associated rudder hydraulic actuator A striped bar illuminates in the...

Page 2038: ...OPERATIONS MANUAL 2 13 20 Page 10 Code 01 JUNE 29 2001 CONTROL PEDESTAL AFT PANEL 1 YAW TRIM KNOB spring loaded to neutral Rotated clockwise or counterclockwise actuates the yaw trim right or left CO...

Page 2039: ...ate an incorrect position of at least one hydraulic actuator of the movable rudder stops system as follows Airplane in flight with movable rudder stops at 15 position Airplane on ground with movable r...

Page 2040: ...0 Page 12 Code 01 AUGUST 24 2001 EICAS INDICATIONS 1 YAW TRIM POSITION Indicated by a green pointer moving on a horizontal scale Center of the scale is zero trimming Each mark represents 50 of trimmin...

Page 2041: ...control column must be pushed and held fully forward and the gust lock lever moved backwards from the FREE to LOCKED position Aside locking the elevators it also restricts both thrust levers to a mini...

Page 2042: ...actory incorporated depending on how the gust lock lever is installed it allows the pilot to choose the thrust lever to have extra travel to be used during taxi For airplanes Post Mod SB 145 27 0126 o...

Page 2043: ...ground maneuvering However the gust lock lever was designed to allow extra travel for one of the thrust levers Airplanes Post Mod SB 145 27 0115 or equipped with an equivalent modification factory in...

Page 2044: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS REVISION 41 2 13 25 Page 3 Code 01 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 TO LOCK...

Page 2045: ...he elevators will be unlocked after approximately 10 seconds The indication lights will illuminate during the unlocking cycle remaining off after that After the indication lights go off pull the contr...

Page 2046: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS REVISION 41 2 13 25 Page 5 Code 01 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 TO UNLOCK...

Page 2047: ...that the locking pins were commanded to unlock the elevator surfaces Illuminates in case of failure Illuminates when it is pressed NOTE For airplanes Post Mod SB 145 27 0125 or with an equivalent mod...

Page 2048: ...ON 41 2 13 25 Page 7 Code 01 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 CONTROL STAND GUST LOCK LEVER Actuated backward locks both elevator and thrust control levers The safety lock...

Page 2049: ...FLIGHT CONTROLS AIRPLANE OPERATIONS MANUAL 2 13 25 Page 8 Code 01 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 2050: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS JUNE 29 2001 2 13 30 Page 1 Code 01 FLAP SYSTEM The flaps are electrically operated consisting of two double slotted flap panels installed to each wing...

Page 2051: ...remaining motor can drive all flap panels at half speed An EICAS message is presented to indicate that flaps are being moved at a lower speed If both motors or control channels fail an EICAS message i...

Page 2052: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS REVISION 18 2 13 30 Page 3 Code 01 FLAP SCHEMATIC...

Page 2053: ...rust lever angle is above 60 and the flaps are not in the certified takeoff position the digits box and pointer turn red and the aural warning TAKEOFF FLAPS sounds In addition only for flaps position...

Page 2054: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS JUNE 29 2001 2 13 30 Page 5 Code 01 CONTROL PEDESTAL AFT PANEL...

Page 2055: ...to 45 with discrete indication on 0 9 18 22 and 45 Colors Box white Digits green except 0 which is white changes to a green dash when flaps are in transit In transit flap position is replaced by the...

Page 2056: ...destroy lift thus providing better braking effectiveness Spoilers are electrically commanded and hydraulically actuated A Spoiler Control Unit is responsible for permitting the spoiler panels to open...

Page 2057: ...EICAS SPEED BRAKE When speed brake is commanded with autopilot engaged the auto pitch trim is provided through the autopilot when the autopilot is not engaged the Spoiler Control Unit provides the aut...

Page 2058: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS REVISION 18 2 13 35 Page 3 Code 01 SPOILER SYSTEM SCHEMATIC...

Page 2059: ...ing logic is not satisfied SPOILER AURAL WARNING TAKEOFF SPOILERS If the airplane is on the ground any thrust lever angle is above 60 and any spoiler speed brake panel is deployed the digits box and p...

Page 2060: ...AIRPLANE OPERATIONS MANUAL FLIGHT CONTROLS JUNE 29 2001 2 13 35 Page 5 Code 01 CONTROL STAND...

Page 2061: ...AUGUST 24 2001 EICAS INDICATIONS 1 SPOILERS INDICATION Displays OPN when any of the surfaces are open or CLD when all of the surfaces are closed Colors Box white CLD white OPN green in normal conditi...

Page 2062: ...n Temperature Control 2 14 10 05 Air Conditioning Distribution 2 14 10 06 Pack Valve Operational Logic 2 14 10 08 EICAS Messages 2 14 10 11 Controls and Indicators 2 14 10 13 Environmental Control Sys...

Page 2063: ...PNEUMATICS AIR CONDITIONING AND PRESSURIZATION AIRPLANE OPERATIONS MANUAL 2 14 00 Page 2 Code 01 REVISION 18 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2064: ...air conditioning system receives air from the pneumatic system and provides conditioned air to the cabin The system is controlled by two Environmental Control Units ECU The pressurization system uses...

Page 2065: ...rovided through the tapping upstream of the HSV An Engine Bleed Valve EBV which is electrically commanded through the Bleed Air Button and pneumatically actuated is installed downstream of the pre coo...

Page 2066: ...pneumatic system s functional logic to allow engine bleed airflow to anti ice system A Cross Bleed Valve CBV which is electrically commanded through the Cross Bleed Knob and pneumatically actuated pr...

Page 2067: ...PNEUMATICS AIR CONDITIONING AND PRESSURIZATION AIRPLANE OPERATIONS MANUAL 2 14 05 Page 2B Code 01 REVISION 29 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2068: ...AIRPLANE OPERATIONS MANUAL PNEUMATICS AIR CONDITIONING AND PRESSURIZATION REVISION 23 2 14 05 Page 3 Code 01 PNEUMATIC SYSTEM SCHEMATIC...

Page 2069: ...cally actuated provides APU bleed control The pneumatic system functional logic automatically closes the ABV whenever any engine is supplying bleed air to the left pneumatic side An APU Check Valve is...

Page 2070: ...AIRPLANE OPERATIONS MANUAL PNEUMATICS AIR CONDITIONING AND PRESSURIZATION JUNE 28 2002 2 14 05 Page 5 Code 01 INTEGRATED PNEUMATIC SYSTEM SCHEMATIC...

Page 2071: ...e respective side of the rear electronic compartment There is no leakage downstream of the respective pre cooler Respective engine N2 is above 56 4 and Respective engine fire extinguishing handle is n...

Page 2072: ...gized There is no massive bleed leakage downstream of the pre cooler or in the Rear Electronic Compartment and Cross Bleed Knob is set to OPEN or Cross Bleed Knob is set to AUTO and one of the followi...

Page 2073: ...PNEUMATICS AIR CONDITIONING AND PRESSURIZATION AIRPLANE OPERATIONS MANUAL 2 14 05 Page 6B Code 01 REVISION 29 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2074: ...P Abnormal low or asymmetric bleed temperature or pre cooler outlet temperature sensor failure CAUTION BLD 1 2 VLV FAIL Disagreement between actual position and commanded position of the associated En...

Page 2075: ...PNEUMATICS AIR CONDITIONING AND PRESSURIZATION AIRPLANE OPERATIONS MANUAL 2 14 05 Page 8 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2076: ...Attendant Panel The air conditioning distribution is performed by the gasper system and general outlets with cross connection between the cockpit and passenger cabin lines This feature associated wit...

Page 2077: ...ry heat exchanger the high pressure cooled air passes through a condenser and a water separator for condensed water removal Spray nozzles uses the separated water to improve the heat exchanger efficie...

Page 2078: ...RAM AIR SECONDARY HEAT EXCHANGER LEFT ECS PACK DUAL TEMPERATURE CONTROL VALVE HEAT EXCHANGER PRIMARY FAN TO OUTSIDE COMPRESSOR TURBINE CONDENSER WATER SEPARATOR FROM RIGHT PACK RECIRCULATION FAN PASSE...

Page 2079: ...nd the ram air valves are opened automatically allowing ram air to be routed to the distribution lines Ram air may also be used to ventilate the airplane interior for cabin smoke evacuation and cabin...

Page 2080: ...ion from the temperature knobs and the duct temperature sensor The manual mode should be used only if a failure occurs in the automatic mode and may be noticed when the temperature is not maintained w...

Page 2081: ...gasper If the duct temperature is below 24 C 75 F the associated temperature switches command the recirculation fans to increase airflow The gasper air subsystem provides air to individual air outlets...

Page 2082: ...2018A DGN GASPER GASPER FOOT VALVES GASPER VALVE GROUND CONNECTION RECIRCULATION FANS UPPER DUCT LOWER DUCT UPPER DUCT LOWER DUCT GASPER FAN AIR DISTRIBUTION VALVES RAM AIR CHECK VALVE RAM AIR VALVE E...

Page 2083: ...lve and No discrete ECS Environmental Control System OFF signal is sent from any related FADEC A or B The FADEC s discrete ECS OFF signals are produced according to the following conditions 1 During T...

Page 2084: ...ctivated for the Pack associated with the operating engine if the pressure altitude is lower than 9700 ft and TAT is above 19 C at sea level decreasing linearly to 5 C at 9700 ft area A in the followi...

Page 2085: ...tically reset pack 2 will be commanded to open 10 seconds after pack 1 opening to avoid passenger discomfort due to packs return On other airplane models if a FADEC commands its associated pack to clo...

Page 2086: ...re above 243 C 470 F or ECU inlet pressure above 55 psig CAUTION PACK 1 2 OVHT Associated ECU outlet temperature above 93 C 200 F PACK 1 2 VLV FAIL RAM AIR VLV FAIL Disagreement between associated val...

Page 2087: ...PNEUMATICS AIR CONDITIONING AND PRESSURIZATION AIRPLANE OPERATIONS MANUAL 2 14 10 Page 12 Code 01 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 2088: ...ntrols the right pack in automatic mode through the Digital Temperature Controller The passenger cabin temperature may be set between 18 C 65 F and 29 C 85 F PULLED Controls the right pack in manual m...

Page 2089: ...on mode of the Cross bleed Valve OPEN Opens the Cross bleed Valve 7 BLEED AIR BUTTON Opens pressed or closes released the associated Engine Bleed Valve A striped bar illuminates inside the button to i...

Page 2090: ...AOM142003A DGN OVERHEAD PANEL 1 2 3 4 5 6 7 8 AIR CONDITIONING PNEUMATIC C H CKPT RECIRC PASS CABIN GASPER WING 1 A I STAB A I STARTER 1 XBLEED WING 2 A I STARTER 2 BLEED 1 APU BLEED BLEED 2 ATTD AUTO...

Page 2091: ...s the bleed air temperature downstream of the pre cooler on the left and right engine Scale and Pointer White for the scale below 260 C 500 F to indicate potentially low thermal energy availability to...

Page 2092: ...MATICS AIR CONDITIONING AND PRESSURIZATION REVISION 38 2 14 10 Page 17 Code 01 AOM 145 1114 EM145AOM142004A DGN ECS CKPT TEMP BLEED TEMP MFD 1 2 3 21 C CABIN TEMP 21 C O O ENVIRONMENTAL CONTROL SYSTEM...

Page 2093: ...tendant s panel 2 PASSENGER CABIN TEMPERATURE CONTROL KNOB OR SLIDING CONTROL Actuates on the passenger cabin temperature controller right ECU in the automatic mode provided the Passenger Cabin Temper...

Page 2094: ...n differential pressure relief 0 3 psi Cabin altitude limitation when in the auto mode 15000 ft maximum The system is normally operated in the automatic mode The manual mode is used in case of automat...

Page 2095: ...ltitude that is the value that the measured cabin altitude must be equal to Cabin altitude rate of change varies according to the different operation sequences Proper operation of the pressurization s...

Page 2096: ...AIRPLANE OPERATIONS MANUAL PNEUMATICS AIR CONDITIONING AND PRESSURIZATION REVISION 19 2 14 15 Page 3 Code 01 CABIN PRESSURE CONTROL SYSTEM SCHEMATIC...

Page 2097: ...rn to the takeoff airport It causes the cabin altitude to continue descending towards the altitude equivalent to 0 2 psi below the takeoff altitude If an altitude of 0 2 psi below the takeoff altitude...

Page 2098: ...RPLANE OPERATIONS MANUAL PNEUMATICS AIR CONDITIONING AND PRESSURIZATION REVISION 19 2 14 15 Page 5 Code 01 AUTOMATIC PREPRESSURIZATION AND TAKEOFF SEQUENCE AUTOMATIC DEPRESSURIZATION SEQUENCE ON GROUN...

Page 2099: ...ft min for EMB 145 Post Mod SB 145 21 0006 or S N 145 050 and on EMB 135 and ERJ 140 models AUTOMATIC DEPRESSURIZATION SEQUENCE ON GROUND This sequence is initiated when the airplane is on the ground...

Page 2100: ...by selecting MAN in the Pressurization Mode Selector Button and rotating the Manual Controller until the desired cabin rate of change is reached The crew is responsible for monitoring cabin differenti...

Page 2101: ...H Sets the landing altitude in the Landing Altitude Indicator Altitude changes in 100 ft steps Holding the selector for more than 5 seconds changes the altitude in a 1000 ft sec rate Landing altitude...

Page 2102: ...ge 9 Code 01 MANUAL CONTROLLER KNOB Selects cabin rate of change between 1500ft min at DN position and approximately 2500ft min at UP position when in the manual operating mode When operating in the A...

Page 2103: ...ft for EICAS version 14 up to 16 from 8400 to 9900 ft for EICAS version 16 5 and above Red from 10000 to 37000 ft 2 DIFFERENTIAL PRESSURE INDICATION Displays the differential pressure between the cabi...

Page 2104: ...rts and a Cabin Pressure Acquisition Module CPAM Both outflow valves receive static pressure signals from static ports for overpressure relief and negative pressure relief functions actuating pneumati...

Page 2105: ...by pressing a Bezel Button on the MFD Display When HIGH ALT mode is selected an indication on MFD Display becomes boxed and the message HI ALT LDG T O will appear on EICAS This message will advise th...

Page 2106: ...Controller schedules a cabin altitude that is the value that the measured cabin altitude must be equal to Cabin altitude rate of change varies according to the different operation sequences Proper ope...

Page 2107: ...ATICS AIR CONDITIONING AND PRESSURIZATION AIRPLANE OPERATIONS MANUAL 2 14 15 Page 4 Code 02 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 CABIN PRESSURE CONTROL SYSTEM SCHE...

Page 2108: ...airplane altitude In the case of takeoff with air conditioning supply the cabin altitude is controlled with an altitude rate of descent equal to 450 ft min In the case of takeoff without air conditio...

Page 2109: ...The cabin altitude rate of change is controlled at different values depending on the scheduled cabin altitude and the airplane vertical speed but is limited to 450 ft min during descent and as followi...

Page 2110: ...TICS AIR CONDITIONING AND PRESSURIZATION REVISION 41 2 14 15 Page 7 Code 02 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 AUTOMATIC PREPRESSURIZATION AND TAKEOFF SEQUENCE AUTOMATIC DEP...

Page 2111: ...s Pre Mod SB 145 21 0006 or 450 ft min and 500 ft min for EMB 145 Post Mod SB 145 21 0006 or S N 145 050 and on and EMB 135 models AUTOMATIC DEPRESSURIZATION SEQUENCE ON GROUND This sequence is initia...

Page 2112: ...tton and rotating the Manual Controller until the desired cabin rate of change is reached The crew is responsible for monitoring cabin differential pressure within acceptable values In manual mode the...

Page 2113: ...g altitude in the Landing Altitude Indicator Altitude changes in 100 ft steps Holding the selector for more than 5 seconds changes the altitude in a 1000 ft sec rate Landing altitude setting from 1500...

Page 2114: ...Refertocoverpagefor details AOM 145 1114 MANUAL CONTROLLER KNOB Selects cabin rate of change between 1500 ft min at DN position and approximately 2500 ft min at UP position when in the manual operati...

Page 2115: ...e 12 Code 02 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 MFD 1 HIGH ALT STATUS INDICATION Displays HIGH ALT activation status Boxed HIGH ALT mode activated Unboxed HIGH A...

Page 2116: ...AIRPLANE OPERATIONS MANUAL PNEUMATICS AIR CONDITIONING AND PRESSURIZATION REVISION 41 2 14 15 Page 13 Code 02 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 MFD HIGH ALT MODE ACTIVATION...

Page 2117: ...37000 14500 to 37000 2 DIFFERENTIAL PRESSURE INDICATION Displays the differential pressure between the cabin interior and the outside regardless of the operating mode Ranges from 0 5 to 10 0 psi with...

Page 2118: ...PLANE OPERATIONS MANUAL PNEUMATICS AIR CONDITIONING AND PRESSURIZATION REVISION 41 2 14 15 Page 15 Code 02 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 PRESSURIZATION INDICATION ON EI...

Page 2119: ...PNEUMATICS AIR CONDITIONING AND PRESSURIZATION AIRPLANE OPERATIONS MANUAL 2 14 15 Page 16 Code 02 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 INTENTIONALLY BLANK...

Page 2120: ...dules When the airplane is energized the inverter modules are turned on supplying power to the recirculation fans The electrical power supply to the recirculation fan 2 exhaust fan 1 and shutoff valve...

Page 2121: ...ir discharged from the cabin When this air flows from the underfloor area to the outflow valves installed on the rear pressure bulkhead it passes through this compartment cooling it During ground oper...

Page 2122: ...AIRPLANE OPERATIONS MANUAL PNEUMATICS AIR CONDITIONING AND PRESSURIZATION JUNE 29 2001 2 14 20 Page 3 Code 01 FORWARD ELECTRONIC BAY COOLING SCHEMATIC...

Page 2123: ...PNEUMATICS AIR CONDITIONING AND PRESSURIZATION AIRPLANE OPERATIONS MANUAL 2 14 20 Page 4 Code 01 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2124: ...passenger cabin air flowing into it the Baggage Ventilation System provides an adequate environment for carrying live animals in the compartment The Baggage Ventilation System is composed of two ambie...

Page 2125: ...PNEUMATICS AIR CONDITIONING AND PRESSURIZATION AIRPLANE OPERATIONS MANUAL 2 14 25 Page 2 Code 01 REVISION 18 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2126: ...perational Logic 2 15 10 03 EICAS Messages 2 15 10 08 Windshield Heating System 2 15 10 09 EICAS Messages 2 15 10 10 Windshield Differentiation 2 15 10 11 Sensor Heating System 2 15 10 13 EICAS Messag...

Page 2127: ...ICE AND RAIN PROTECTION AIRPLANE OPERATIONS MANUAL 2 15 00 Page 2 Code 01 REVISION 41 Copyright byEmbraer Refertocoverpagefordetails AOM 145 1114 INTENTIONALLY BLANK...

Page 2128: ...are Wing and horizontal stabilizer leading edges Engine air inlet lips The electrically heated areas are Windshields Pitot tubes Pitot static tube AOA sensors TAT probes ADCs and pressurization static...

Page 2129: ...ICE AND RAIN PROTECTION AIRPLANE OPERATIONS MANUAL 2 15 05 Page 2 Code 01 REVISION 41 Pages 3 and 4 Deleted Copyright byEmbraer Refertocoverpagefordetails AOM 145 1114 ICE AND RAIN PROTECTION SYSTEM...

Page 2130: ...check for ice accumulation Each subsystem comprises an anti icing valve pressure regulating shutoff valve A restrictor limits the airflow rate supplied by the Pneumatic System It is monitored by pres...

Page 2131: ...d by buttons located on the overhead panel On the ground the FADEC incorporates an automatic logic to reduce the maximum available thrust to avoid a sudden engine thrust loss during lift off even with...

Page 2132: ...prevent structural damage caused by surface heating except during ice detection testing The ice detection test should not be activated for more than 15 seconds The Engine Anti icing Valves receive an...

Page 2133: ...PLANE OPERATIONS MANUAL 2 15 10 Page 4 Code 01 REVISION 39 AOM 145 1114 EM145AOM152002A DGN CHANNELS ZONE JET ZONE CHANNELS ZONE PICCOLO TUBE EXHAUSTION OUTLET REAR REAR BAY SPAR NOSE BAY BAFFLE WING...

Page 2134: ...BE AIRFLOW RESTRICTOR LOW PRESSURE SENSOR SWITCH WING ANTI ICING VALVE RIGHT WING DIFFERENTIAL PRESSURE SENSOR FROM PNEUMATIC SYSTEM DIFFERENTIAL PRESSURE SWITCH P 2 P 2 OVERPRESSURE DIFFERENTIAL PRES...

Page 2135: ...ESTRICTOR LOW PRESSURE SENSOR SWITCH WING ANTI ICING VALVE PICCOLO TUBE AIRFLOW RESTRICTOR LOW PRESSURE SENSOR SWITCH WING ANTI ICING VALVE RIGHT WING DIFFERENTIAL PRESSURE SENSOR FROM PNEUMATIC SYSTE...

Page 2136: ...LOW PRESSURE SWITCH AIRFLOW RESTRICTOR EXHAUSTION OUTLET EXHAUSTION OUTLET PICCOLO TUBE DIFFERENTIAL PRESSURE SWITCH OVERPRESSURE HORIZONTAL STABILIZER ANTI ICING SYSTEM SCHEMATIC EM145AOM152006A DGN...

Page 2137: ...ICE SWITCH OFF Any Bleed Air Thermal anti icing button turned off CAUTION E1 2 A ICE FAIL Low pressure condition Valve failure Any switch failure Overpressure condition Any system failure NO ICE A ICE...

Page 2138: ...yer which functions as an electric resistor Individual buttons located on the overhead panel control left and right windshield heating Separate power supplies are provided for each windshield heating...

Page 2139: ...controller automatically increase power input to maintain the temperature at 43 C anti ice mode If both ice detectors are inoperative the Override knob on the Overhead Panel set to ALL position provid...

Page 2140: ...TIATION SIERRACIN WINDSHIELD Sierracin windshields can be easily identified by their green colored tint and by the positions of the bus bars to which the heater filaments are attached in the vertical...

Page 2141: ...01 REVISION 39 AOM 145 1114 PPG WINDSHIELD PPG windshields can be easily identified by the positions of the bus bars to which the heater filaments are attached in the horizontal direction as shown bel...

Page 2142: ...airplanes Pre Mod SB 145 30 0028 TAT 1 and 2 are heated provided either Engine 1 or 2 anti icing subsystem is functioning or airplane is in flight the TAT sensor normal range of operation is from 99...

Page 2143: ...the sensor heating is inoperative These messages are inhibited during the takeoff and approach phases EICAS MESSAGES TYPE MESSAGE MEANING PITOT 1 2 3 INOP Associated sensor heating inoperative with a...

Page 2144: ...INLET ANTI ICING BUTTONS Turns off released or permits pressed the automatic activation of the associated engine air inlet anti icing subsystem A striped bar illuminates inside the button to indicate...

Page 2145: ...ight button controls the Pitot tube 2 AOA 2 vane TAT 2 probe and ADC static ports 2 and 4 When pressed the associated sensor heating system operates in the automatic mode according to its functional l...

Page 2146: ...em NOTE If ground speed is equal or above 25 kt and an icing condition is detected wing and horizontal stabilizer anti icing subsystems are turned on The engine anti icing subsystem is turned on as so...

Page 2147: ...ION 39 AOM 145 1114 EM145AOM152007A DGN OVERHEAD PANEL 1 2 3 4 5 7 6 ICE PROTECTION PITOT 2 SENSORS PITOT 1 PITOT 3 WINDSHIELD 1 2 ICE DETECTION AUTO ENG 2 TAT 2 AOA 2 TAT 1 AOA 1 1 ALL OVERRIDE TEST...

Page 2148: ...duction refer to Stall Protection System on Section 2 4 Crew Awareness and an advisory message to be presented on the EICAS During ice encounters the icing signal remains active during 60 seconds Simu...

Page 2149: ...on refer to Stall Protection System on Section 2 4 Crew Awareness and an advisory message to be presented on the EICAS During ice encounters the icing signal remains active during 60 seconds Simultane...

Page 2150: ...s its own independent power supply and a four position knob on the overhead panel WINDSHIELD WIPER CONTROL PANEL IF APPLICABLE 1 WINDSHIELD WIPER SELECTOR KNOB TIMER Provides intermittent operation of...

Page 2151: ...AIRPLANE OPERATIONS MANUAL ICE AND RAIN PROTECTION REVISION 41 2 15 15 Page 3 Code 01 Copyright byEmbraer Refertocoverpagefordetails AOM 145 1114 WINDSHIELD WIPER CONTROL PANEL...

Page 2152: ...ICE AND RAIN PROTECTION AIRPLANE OPERATIONS MANUAL 2 15 15 Page 4 Code 01 REVISION 41 Copyright byEmbraer Refertocoverpagefordetails AOM 145 1114 INTENTIONALLY BLANK...

Page 2153: ...OS Mask 2 16 10 08 Controls and Indicators PURITAN Mask 2 16 10 10 Smoke Goggles 2 16 10 12 Passenger Oxygen 2 16 15 01 Controls and Indicators 2 16 15 05 Portable Oxygen Cylinder 2 16 20 01 Protectiv...

Page 2154: ...OXYGEN AIRPLANE OPERATIONS MANUAL 2 16 00 Page 2 Code 01 OCTOBER 02 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2155: ...gh pressure and distributed at low pressure to the masks The passengers oxygen system is supplied through chemical oxygen generators which is distributed through dispensing units in several different...

Page 2156: ...OXYGEN AIRPLANE OPERATIONS MANUAL 2 16 05 Page 2 Code 01 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 NTENTIONALLY BLANK...

Page 2157: ...at the ON position supplies the crew distribution lines at low pressure rate 70 psi A relief valve opens if the pressure exceed 90 psi The cockpit is provided with a quick donning diluter demand type...

Page 2158: ...OXYGEN AIRPLANE OPERATIONS MANUAL 2 16 10 Page 2 Code 01 REVISION 20 FLIGHT CREW OXYGEN SYSTEM SCHEMATIC...

Page 2159: ...AIRPLANE OPERATIONS MANUAL OXYGEN OCTOBER 02 2001 2 16 10 Page 3 Code 01 MAIN OXYGEN CYLINDER...

Page 2160: ...OXYGEN AIRPLANE OPERATIONS MANUAL 2 16 10 Page 4 Code 01 OCTOBER 02 2001 OXYGEN SERVICE PANEL...

Page 2161: ...2 minutes for pilot copilot and observer ECS PAGE ON MFD 1 ANALOGIC OXYGEN PRESSURE INDICATION Pointer Green between 410 to 1850 psi Amber between 250 to 400 psi Red between 0 to 240 psi 2 DIGITAL OXY...

Page 2162: ...brought to open position thus allowing the oxygen flow to the mask After the mask has been taken out of the stowage box the doors can be closed without interrupting oxygen supply to the mask To stop...

Page 2163: ...e hose and the inflation control valve red ears Pull the mask out of the box Press the inflation control valve red ears firmly The harness inflates rapidly and takes a shape large and rigid enough to...

Page 2164: ...OL pilot and copilot masks only When actuated forward opens the venting valve A red band is visible to indicate that the control is actuated 5 HARNESS INFLATION CONTROL VALVE red ear When pressed infl...

Page 2165: ...AIRPLANE OPERATIONS MANUAL OXYGEN OCTOBER 02 2001 2 16 10 Page 9 Code 01 MASK STOWAGE BOX CREW MASK EROS MASK...

Page 2166: ...ygen is supplied to the mask 4 PURGE VALVE pilot and copilot masks only Automatically opens when the smoke goggles are donned Supplies oxygen only in EMERGENCY position 5 FLOW INDICATOR observer mask...

Page 2167: ...AIRPLANE OPERATIONS MANUAL OXYGEN OCTOBER 02 2001 2 16 10 Page 11 Code 01 MASK STOWAGE BOX CREW MASK PURITAN MASK...

Page 2168: ...mask shell and manually actuated by the user allows direct communication between venting orifice and goggles When mask regulator is selected to emergency position a metered oxygen flow will be directe...

Page 2169: ...he right lateral console above the mask stowage box of the copilot The system is automatically activated provided the Passenger Oxygen Selector Knob is set to the AUTO position and cabin pressure alti...

Page 2170: ...here is no way to stop it CAUTION ONCE ACTUATED EACH CHEMICAL GENERATOR SUPPLIES OXYGEN CONTINUOUSLY WHETHER THE MASKS CONNECTED TO IT ARE BEING USED OR NOT NOTE When oxygen is supplied high temperatu...

Page 2171: ...AIRPLANE OPERATIONS MANUAL OXYGEN REVISION 41 2 16 15 Page 3 Code 01 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 PASSENGER OXYGEN SYSTEM SCHEMATIC...

Page 2172: ...OXYGEN AIRPLANE OPERATIONS MANUAL 2 16 15 Page 4 Code 01 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 DISPENSING UNITS PASSENGER MASKS...

Page 2173: ...oyment of passenger masks Also resets oxygen ON indicator and passenger cabin signs after system activation either on automatic or manual mode AUTO Automatically deploys the passenger masks provided t...

Page 2174: ...OXYGEN AIRPLANE OPERATIONS MANUAL 2 16 15 Page 6 Code 01 REVISION 41 Copyright by Embraer Refertocoverpagefor details AOM 145 1114 PASSENGER OXYGEN CONTROL PANEL...

Page 2175: ...permit the connection of the continuous flow masks furnished in the cylinder bag The supplied masks when connected to the bottle are designed to deliver a maximum of 4 liters per minute of oxygen The...

Page 2176: ...OXYGEN AIRPLANE OPERATIONS MANUAL 2 16 20 Page 2 Code 01 REVISION 20 INTENTIONALLY BLANK...

Page 2177: ...MENT The airplane is equipped with three EROS or PURITAN smoke hood type Protective Breathing Equipment PBE units The PBE unit is an emergency equipment that offers a 15 minute minimum oxygen supply f...

Page 2178: ...ing structures or interiors parts The smoke hood is stowed inside a vacuum sealed aluminized bag itself contained and attached to the bottom internal side of a rigid flat orange box that is provided w...

Page 2179: ...AIRPLANE OPERATIONS MANUAL OXYGEN OCTOBER 02 2001 2 16 25 Page 3 Code 01 HOOD SCHEMATIC AND STOWAGE EROS...

Page 2180: ...o disengage the cover Locate red I D tag and pull sharply to tear open vacuum sealed bag 2 Pull PBE out of sealed bag and shake hood to open 3 Place both hands inside the neckseal opening with palms f...

Page 2181: ...AIRPLANE OPERATIONS MANUAL OXYGEN OCTOBER 02 2001 2 16 25 Page 5 Code 01 HOOD SCHEMATIC AND STOWAGE PURITAN...

Page 2182: ...OXYGEN AIRPLANE OPERATIONS MANUAL 2 16 25 Page 6 Code 01 OCTOBER 02 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2183: ...emperature For additional oxygen consumption refer to Additional Pressure Required Table to calculate how much Additional Oxygen Cylinder Pressure will be required for dispatch ADDITIONAL OXYGEN PRESS...

Page 2184: ...temperature and go vertically up to the desired pressure at 21 C From the intersection point trace to the left to read the indicated gauge pressure to be attained To use the chart for dispatching purp...

Page 2185: ...AIRPLANE OPERATIONS MANUAL OXYGEN REVISION 36 2 16 30 Page 3 Code 01 AOM 145 1114 OXYGEN PRESSURE CORRECTION...

Page 2186: ...21 C 70 F conditions For different temperatures the Oxygen Pressure Correction chart must be used to obtain the pressure at 21 C and then see what is the number of the remaining oxygen mask tests EXA...

Page 2187: ...AIRPLANE OPERATIONS MANUAL OXYGEN REVISION 36 2 16 30 Page 5 Code 01 AOM 145 1114 NOTE The Oxygen Consumption chart has been plotted for 21 C 70 F conditions OXYGEN CONSUMPTION...

Page 2188: ...OXYGEN AIRPLANE OPERATIONS MANUAL 2 16 30 Page 6 Code 01 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 2189: ...01 SECTION 2 17 FLIGHT INSTRUMENTS TABLE OF CONTENTS Block Page General 2 17 05 01 Air Data System ADS 2 17 10 01 Flight Instruments 2 17 15 01 Standby Instruments 2 17 20 01 Radio Altimeter System 2...

Page 2190: ...FLIGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 00 Page 2 Code 01 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2191: ...tional flight data information is presented on the Primary Flight Display PFD Standby electromechanical instruments are provided as backup should there occur a complete failure in the electronic fligh...

Page 2192: ...FLIGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 05 Page 2 Code 01 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2193: ...nd Rain Protection The ADSs 1 and 2 interface with the airplane s systems through the ADCs as follows IC 600 Both ADCs supply pressure altitude barometrically corrected altitude true airspeed calibrat...

Page 2194: ...system RUDDER SYSTEM Both ADCs supply the rudder system with the calibrated airspeed trip point AWU Both ADCs supply the AWU with the overspeed warning output The ADCs functional test mode is entered...

Page 2195: ...AIRPLANE OPERATIONS MANUAL FLIGHT INSTRUMENTS REVISION 28 2 17 10 Page 3 Code 01 AIR DATA SYSTEMS SCHEMATIC...

Page 2196: ...to the respective ADC Four Static ports supply static pressure to both ADCs The Pitot Static tube 3 supplies total air pressure to the Standby Airspeed Indicator and static pressure to the Standby Air...

Page 2197: ...AIRPLANE OPERATIONS MANUAL FLIGHT INSTRUMENTS JUNE 29 2001 2 17 10 Page 5 Code 01 ADS SENSORS SCHEMATIC ADS SENSORS POSITIONING...

Page 2198: ...olution of 1 C In the event of ADC failure or invalid TAT the digits are replaced by three amber dashes 3 TRUE AIRSPEED TAS INDICATION The TAS is presented as a digital readout in knots Colors Digits...

Page 2199: ...AIRPLANE OPERATIONS MANUAL FLIGHT INSTRUMENTS JUNE 29 2001 2 17 10 Page 7 Code 01 ADS INDICATIONS ON THE MFD ADS INDICATION ON THE PFD...

Page 2200: ...FLIGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 10 Page 8 Code 01 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2201: ...rther information on these systems and indications refer to section 2 18 Navigation and Communication Slip Skid indicator 6 is a purely mechanical system 2O 2O 1O 1O 1O 1O 36O 33 N 3 O 3 2 1 1 2 3 1OO...

Page 2202: ...window and the digital Mach readout will be displayed in red and an aural warning will be triggered If the acceleration trend vector exceeds VMO or MMO the digits in the airspeed window and the digit...

Page 2203: ...ttom portion of the airspeed tape in the form of a digital indication Upon power up the digital indications for the set bugs are dashes 5 MACH NUMBER DIGITAL INDICATION Color Green for normal airspeed...

Page 2204: ...een for normal airspeeds Amber for VMO MMO Red from VMO MMO to higher airspeeds Ranges from 40 to 400 KIAS with a resolution of 1 KIAS 8 AIRSPEED COMPARISON MONITOR DISPLAY Color amber Label IAS Displ...

Page 2205: ...AL FLIGHT INSTRUMENTS REVISION 39 2 17 15 Page 5 Code 01 AOM 145 1114 EM145AOM172007A DGN 1 PFD 22O 2OO 26O 28O 26O O 24 I A S O A 2 R 1 A REFER TO SECTION 2 19 2 3 4 5 6 7 8 41O M AUTOPILOT AP AIRSPE...

Page 2206: ...ments the associated airspeed value and moves the associated bug accordingly if the bug is in view 3 REFERENCE SPEED BUTTONS V1 VR V2 AP Allows selection of V1 V2 VR or AP speeds for setting purposes...

Page 2207: ...N BUTTON Returns the MFD to the MAIN Menu If any of the speeds are displayed with both surrounding inner and outer boxes pressing the RTN Button removes the inner box before returning the menu to the...

Page 2208: ...ft The vertical tape moves behind the current altitude window and displays a range of 550 ft from the actual altitude The vertical tape displays digital altitude every 200 ft for altitudes from zero...

Page 2209: ...rough a raster band that will be displayed on the bottom of the altitude tape in case the radio altitude is below 550 ft Covers the lower half of the altitude tape when the airplane is on ground 7 BAR...

Page 2210: ...OO 22O 2OO DTK H 25 HDG GSPD IN OO 29 92 OO O O 1 STD BARO IN HPA LNAV VS 26O WX 5O 3 5 28O 26O O 24 FMS APP KDVT DR VOR1 ADF2 TGT 245KTS MAG2 MSG 3OOO 2OO RA 359 41O 12 5 M I A S A L T AP YD G S ASEL...

Page 2211: ...r information on TCAS refer to Section 2 4 Crew Awareness 1 ANALOGIC VERTICAL SPEED INDICATION Color Scale white Pointer green Ranges from 3000 to 3000 ft min Scale has marks every 500 ft min up to 30...

Page 2212: ...FLIGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 15 Page 12 Code 01 REVISION 39 Pages 13 and 14 deleted AOM 145 1114 EM145AOM172010A DGN PFD O 3 2 1 1 2 3 1OOO 1 2 VERTICAL SPEED INDICATION ON PFD...

Page 2213: ...l units and most of them are available even in case of total loss of electrical power Optionally the conventional units may be replaced by a single display the Integrated Standby Instruments System IS...

Page 2214: ...015 025 Full dots every ten degrees 010 020 Full dots and respective magnetic heading indication every 030 030 060 Full dots and the N E S and W characters at the respective cardinal points North Eas...

Page 2215: ...ing over a fixed scale calibrated in knots The scale is graduated form 40 to 360 KIAS as follows Half dots between the tens dots 45 55 65 Full dots every ten dots 40 50 60 Full dots and respective air...

Page 2216: ...titude Ranges from 1000 ft to 50000 ft with the following increments Right drum counter is numbered at 100 ft intervals Center drum counter is numbered at 1000 ft intervals Left drum counter is number...

Page 2217: ...AIRPLANE OPERATIONS MANUAL FLIGHT INSTRUMENTS REVISION 37 2 17 20 Page 5 Code 01 AOM 145 1114 STANDBY ALTIMETER TYPICAL...

Page 2218: ...or speed is completely stabilized which occurs within 3 minutes after it is uncaged Any adjustment during the flight although not normally required should be made by momentarily caging the indicator w...

Page 2219: ...e field below the horizon line is indicated in black dive and above in light blue climb 4 CAGE KNOB Pull to the fully extended position rotate clockwise and release at the detent position to cage the...

Page 2220: ...FLIGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 20 Page 8 Code 01 REVISION 39 AOM 145 1114 STANDBY ATTITUDE INDICATOR...

Page 2221: ...he ISIS relies on 28 V DC power provided by the Backup Hot Bus In case of an electrical emergency it will operate solely on the airplane batteries for approximately 240 minutes For the EMB 145 XR mode...

Page 2222: ...y processing static pressure sensed by Pitot Static tube 3 Altitude is displayed in tape format Pushing the STD button sets the ISIS reference barometric pressure to standard QNE The barometric pressu...

Page 2223: ...s of the airspeed tape and Mach number display are green when the airspeed and Mach number are lower than VMO MMO and red when the airspeed and Mach number are equal to or greater than VMO MMO 4 ROLL...

Page 2224: ...tings When the knob is turned at a slow rate the value increases in 0 01 inHg or 1 hPa increments When turned at a faster rate the increment is in 0 05 inHg or 5 hPa steps 11 MAGNETIC HEADING Given by...

Page 2225: ...S MANUAL FLIGHT INSTRUMENTS REVISION 37 2 17 20 Page 13 Code 01 AOM 145 1114 14 AIRCRAFT SYMBOL Displayed on the center of the horizon area Black symbol surrounded by a yellow area INTEGRATED STANDBY...

Page 2226: ...SIS failure to align The system s electrical power must be reset Make sure the airplane is stationary during subsequent ISIS alignment If during any other phase of operation indicates loss of attitude...

Page 2227: ...ed with the associated code failure The associated parameters are saved in memory for future equipment maintenance Report to maintenance SPD white digits over a red filled box Indicates loss of airspe...

Page 2228: ...FLIGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 20 Page 16 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 2229: ...ystem RA 2 can be installed The decision height setting is provided through the decision height setting knob on the Displays Control Panel The decision height and the associated RA label are displayed...

Page 2230: ...upper left side of the attitude sphere An amber MIN label is displayed in the RA Minimum annunciator The label flashes for about 5 seconds and then becomes steady An amber RA comparison label is disp...

Page 2231: ...sides are tested at the same time E GPWS INOP WINDSHEAR INOP When released the PFD indications resume the initial condition and the EGPWS voice message may occur TOO LOW TERRAIN On the ground pressing...

Page 2232: ...for 10 seconds and then becomes steady The RA Minimum annunciator is armed when the following conditions occur simultaneously Airplane in flight Radio Altitude and decision height are valid Radio Alt...

Page 2233: ...ay In the event of a Radio Altimeter failure the decision height digits are replaced by amber dashes 4 RADIO ALTITUDE COMPARISON MONITOR DISPLAY Label RA Color amber Displayed when the difference betw...

Page 2234: ...FLIGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 25 Page 6 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 2235: ...AIRPLANE OPERATIONS MANUAL FLIGHT INSTRUMENTS REVISION 37 2 17 25 Page 7 Code 01 AOM 145 1114 RADIO ALTIMETER INDICATIONS ON THE PFD...

Page 2236: ...FLIGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 25 Page 8 Code 01 REVISION 37 AOM 145 1114 INTENTIONALLY BLANK...

Page 2237: ...e pressings control start stop and reset of the chronometer indicator and pointer providing the following START Replaces elapsed time by chronometer indications starting its counting STOP Freezes chro...

Page 2238: ...ses the selector to cycle between GMT minutes GMT hours LOC minutes LOC hours days months and years with power up the year is pre selected to 90 Once the function is selected it flashes on and off the...

Page 2239: ...FLIGHT INSTRUMENTS REVISION 38 2 17 30 Page 3 Code 01 AOM 145 1114 EM145AOM172018A DGN T R IM DO W N U P A P T R I M P U S H E R D I S C S Y N C A P FD M IC HO T O F F P T T C HRO O N S T A R T S T O...

Page 2240: ...IGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 30 Page 4 Code 01 REVISION 38 AOM 145 1114 EM145AOM172019A DGN CHR GMT LOC ET CHR Mo Dy 0 45 15 30 ET DATE GMT SET LO FLT NR MAIN PANEL 1 2 3 4 6 5 CLO...

Page 2241: ...in the memories with exception of the ET and chronometer functions Display may also blank when a failure exists in the instrument DIGITAL CHRONOMETER CLOCK CONTROLS AND INDICATORS 1 SEL ET PUSH BUTTON...

Page 2242: ...30 Page 6 Code 01 REVISION 38 AOM 145 1114 CHR MODE CHR RST SEL ET 1 2 INT 3 4 6 5 TR IM DO W N U P A P T R I M P U S H E R D I S C S Y N C A P FD M IC HO T O F F P T T C HRO O N S T A R T S TO P R E...

Page 2243: ...s optional An FDR malfunction is detected by means of the power up built in test or the continuous self checking test An EICAS message is generated to indicate the failure The CSMU is a shock and heat...

Page 2244: ...d DAU 2 to FDR and CMC without pilot action as soon as the airplane is energized All the information is recorded in a removable rewritable magnetic optical disk thus reducing the time for ground data...

Page 2245: ...AIRPLANE OPERATIONS MANUAL FLIGHT INSTRUMENTS REVISION 33 2 17 35 Page 3 Code 01 FLIGHT DATA RECORDER SYSTEM SCHEMATIC for airplanes not equipped with AFDAU...

Page 2246: ...FLIGHT INSTRUMENTS AIRPLANE OPERATIONS MANUAL 2 17 35 Page 4 Code 01 REVISION 33 FLIGHT DATA RECORDER SYSTEM SCHEMATIC for airplanes equipped with AFDAU FDR 88 parameters...

Page 2247: ...Control Head 2 18 13 01 Normal Mode 2 18 13 01 Emergency Mode 2 18 13 01 Self Test 2 18 13 01 TBCH Controls and Indicators 2 18 13 02 Digital Audio Panel 2 18 15 01 Normal Mode 2 18 15 01 Emergency Mo...

Page 2248: ...I CMU 2 18 24 01 CMU Normal Operation 2 18 24 04 CMU Abnormal Operation 2 18 24 04 CMU Controls and Indicators 2 18 24 06 Printer Controls and Indicators 2 18 24 08 Cockpit Voice Recorder 2 18 25 01 S...

Page 2249: ...Radar System 2 18 45 01 General 2 18 45 03 Weather Radar Normal Operation 2 18 45 04 Interpreting Weather Radar Images 2 18 45 04 Radar Warm Up Period 2 18 45 06 Ground Operation Precautions 2 18 45 0...

Page 2250: ...Transceiver XT 6011 2 18 90 02 Remote Control Unit GB 6500 2 18 90 03 Operation 2 18 90 04 Built In Test BIT Design 2 18 90 04 Normal Operation 2 18 90 04 Tactical U VHF Selection 2 18 90 06 Abnormal...

Page 2251: ...stem Aural Warning Unit and Cockpit Voice Recorder Optional communication equipment includes an HF transceiver Third VHF NAV COM SELCAL and Aircraft Communication Addressing and Reporting System ACARS...

Page 2252: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 01 Page 2 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2253: ...ing major components Remote mounted Integrated Navigation Unit INU Integrated Communication Unit ICU Cockpit Mounted 2 Radio Management Unit RMU 1 Tuning Backup Control Head TBCH 3 Digital Audio Panel...

Page 2254: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 05 Page 2 Code 01 AUGUST 24 2001 RMS SCHEMATIC...

Page 2255: ...ay be provided in this unit VHF Communication Transceiver Module TR 850 This module is a conventional VHF COM transceiver that operates in the frequency range of 118 to 136 975 MHz Mode S Diversity Tr...

Page 2256: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 07 Page 2 Code 01 REVISION 17 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2257: ...nventional ILS Also includes a 75 MHz marker beacon receiver which detects and transmits the tones of the marker beacons to the Audio System DME Transceiver Module DM 850 The DME module is a six chann...

Page 2258: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 09 Page 2 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2259: ...play for the main panel PFDs and MFDs In this condition the main panel is turned off and the NAVIGATION Backup Page which presents basic navigation information may be accessed through RMU page RMU PAG...

Page 2260: ...adjust the active and preset frequency transmission reception mode mode of operation squelch level and Transmission TX power ATC TCAS CONTROL PAGE The ATC TCAS Control Page allows the pilot to select...

Page 2261: ...e of the radios This page is not available in flight RMU NORMAL OPERATION RMU SELF TEST On the ground the RMS performs a self test each time power is applied after power off periods greater than 10 se...

Page 2262: ...n The pilot should verify the operation of the function CROSS SIDE OPERATION The RMU is provided with a feature called cross side operating mode This feature allows the RMU to be changed from its norm...

Page 2263: ...P label indicating that the new preset frequency has been stored in the indicated memory location Placing the yellow cursor box to enclose the MEMORY label by pressing a second time the Line Select Bu...

Page 2264: ...Squelch Control Button labeled SQ on the RMU control bezel Pressing this button will cause the COM radio to open its squelch and allow any noise or signal present in the receiver to be heard in the Au...

Page 2265: ...channels is paired with the VOR active frequency and one other with the preset VOR frequency However pressing the DME Select Button labeled DME on the RMU Bezel Panel will enable the DME to be tuned i...

Page 2266: ...d its use will take no effect Therefore the UD LD and CW modes should not be selected Simplex Operation means that the transmission and reception frequencies are the same while Split or Semi duplex Op...

Page 2267: ...HF reception with one system is inhibited because the other system is transmitting or has just finished a transmission SQ Squelch is opened with the SQ function key squelch test mode YELLOW TX INH One...

Page 2268: ...ht rotation of the knob The RMU also has the capability of storing an ADF frequency This is accomplished by selecting the desired ADF frequency and then pressing the Memory Storage Button on the RMU B...

Page 2269: ...a non standby mode is selected Once the mode annunciation is surrounded pressing the Transfer Button 1 2 will select which transponder will be in operation e g 1 ATC ON to 2 ATC ON The transponder ope...

Page 2270: ...to enter or exit Direct Tune Mode for COM and NAV 3 FREQUENCY TUNING OUTER KNOB Allows the data field enclosed by the cursor to be modified The data may be frequency setting stored frequencies or mod...

Page 2271: ...TCAS data in the cross side display With the cursor in the HF window pressing this button toggles the display between HF1 and HF2 tuning pages There will be dashes in the window if the HF in view is n...

Page 2272: ...anual dimming control can be disabled by pressing the Dimming Button again or any Line Select Button 11 TRANSPONDER IDENTIFICATION MODE BUTTON Selects the Transponder Identification Response Mode The...

Page 2273: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 15 Code 01 RMU BEZEL PANEL...

Page 2274: ...NE Page press the Line Select Button adjacent to this label Color Green 4 SYS SELECT PAGE LABEL To access the SYS SELECT Page press the Line Select Button adjacent to this label Color Green 5 MAINTENA...

Page 2275: ...Page press the Line Select Button adjacent to the desired page Color Green 9 HF CONTROL only for KHF 1050 To access the HF Control Page press the Line Select Button adjacent to the desired page Color...

Page 2276: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 11 Page 18 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 2277: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 19 Code 01 PAGE MENU...

Page 2278: ...e scrolled by using the Frequency Tuning Knobs 2 COM WINDOW CONTROL SIDE IDENTIFICATION Identifies the window and which source equipment side 1 or 2 is active in that RMU Colors White for on side sour...

Page 2279: ...any failure in the associated source 7 DME HOLD MODE ANNUNCIATION Indicates that the DME is in Hold Mode and the active DME channel is selected separately from the active VOR ILS frequency Color Yello...

Page 2280: ...Frequency Tuning Knobs when the yellow cursor box is located in this field Color Green 13 HF WINDOW only for KHF 1050 Identifies the window and which source equipment side 1 or 2 is active in that RMU...

Page 2281: ...de as selected through the Frequency Tuning Knobs when the yellow cursor box is located in this field Pressing the Line Select Button beside this field will alternate between the pre selected transpon...

Page 2282: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 11 Page 24 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 2283: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 25 Code 01 RMU RADIO PAGE...

Page 2284: ...ly active Color White 3 SQUELCH MODE INDICATION Indicates if squelch is open Color Yellow 4 MEMORY PAGE SELECTED ANNUNCIATION Indicates that the Memory Page is selected Color Green 5 MEMORIES DISPLAY...

Page 2285: ...ct Button associated with the Insert prompt is pressed Color Green 7 MEMORY DELETE PROMPT To delete a frequency from the memory press the Line Select Button adjacent to the line associated with the fr...

Page 2286: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 11 Page 28 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 2287: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 29 Code 01 RMU COM MEMORY PAGE...

Page 2288: ...ther or not the Radio System interfaces with the FMS Color Yellow NOTE When the VOR or the ILS frequency is auto tuned by the FMS a magenta VOR or ILS frequency and a magenta AUTO label will be displa...

Page 2289: ...ct Button associated with the Insert prompt is pressed Color Green 7 MEMORY DELETE PROMPT To delete a frequency from the memory press the Line Select Button adjacent to the line associated with the fr...

Page 2290: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 11 Page 32 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 2291: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 33 Code 01 RMU NAV MEMORY PAGE...

Page 2292: ...tive Receive and Transmission frequency If in Emergency or ITU mode holding the Upper Line Select Button displays the corresponding frequency and emission mode and releasing it returns the display to...

Page 2293: ...cted by the cursor box Color Green 9 LOAD PROMPT Pressing the associated Line Select Button loads the information from the memory location selected by the cursor box into the active channel Color Gree...

Page 2294: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 11 Page 36 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 2295: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 33 2 18 11 Page 37 Code 01 HF MEMORY PAGE only for KHF 1050...

Page 2296: ...the display to the preset channel Pressing the Lower Line Select Button positions the cursor around the preset frequency If the cursor is already positioned in the preset frequency the Lower Line Sel...

Page 2297: ...ne Select Button positions the cursor around the Receive Frequency It also toggles between the active Receive and Transmission frequency If in Emergency or ITU mode holding the Upper Line Select Butto...

Page 2298: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 11 Page 40 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 2299: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 33 2 18 11 Page 41 Code 01 HF CONTROL PAGE only for KHF 1050...

Page 2300: ...n case of Dual installation press the HF2 button on the Pilot or Copilot position to toggle between HF1 and HF2 radio system The HF1 radio system is selected when the button is unlit and the HF2 is se...

Page 2301: ...r RA target condition exists MANUAL cyan All traffic targets displayed within the viewing airspace 3 FLIGHT ID Allows Mode S coding to reflect the current flight s call sign The outer tuning knob move...

Page 2302: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 11 Page 44 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 2303: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 45 Code 01 RMU ATC TCAS CONTROL PAGE...

Page 2304: ...mpass card is presented only in arc partial format The selected course and the DME distance to station are boxed NAV and ADF active frequencies are also presented 1 ACTIVE NAV FREQUENCY 2 BEARING 1 PO...

Page 2305: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 47 Code 01 RMU NAV BACKUP PAGE...

Page 2306: ...TEMPERATURE ITT Indicates the temperature in degrees Celsius 4 N2 INDICATION CORE SPEED Displays N2 speed in RPM percentage 5 FUEL FLOW INDICATION FF Indicates fuel flow in PPH or KPH 6 OIL PRESSURE I...

Page 2307: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 49 Code 01 RMU ENGINE BACKUP PAGES...

Page 2308: ...nd COM 2 status regarding bandwidth selection Pressing the Line Select Button beside the COM 1 COM 2 line field will toggle the receiver bandwidth from WIDE 2 digits at the right of the decimal point...

Page 2309: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 51 Code 01 RMU SYSTEM SELECT PAGE...

Page 2310: ...g test fails the RMU is not fully operable PRI BUS Full RMU com munications with all COMs NAVs and cross side RMU cannot be established on the primary bus 1 Check that all radio circuit breakers are o...

Page 2311: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 53 Code 01 RMU MAINTENANCE PAGE POWER ON SELF TEST...

Page 2312: ...EVISION 31 MAINTENANCE PAGE PILOT ACTIVATED SELF TEST 1 SYSTEM TEST IDENTIFICATION Indicates which unit is being tested Color Amber 2 TEST RESULT INDICATION Indicates whether the tested system is oper...

Page 2313: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 11 Page 55 Code 01 RMU MAINTENANCE PAGE PILOT ACTIVATED SELF TEST...

Page 2314: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 11 Page 56 Code 01 REVISION 31 INTENTIONALLY BLANK...

Page 2315: ...RMU 1 NAV and COM active frequencies using the RMU cross side operational mode see 2 18 11 page 4 EMERGENCY MODE When the TBCH is set to the Emergency Mode the Radio Management System will accept onl...

Page 2316: ...NAV AUDIO ON ANNUNCIATION Indicates that the NAV audio is selected on 5 EMERGENCY MODE ANNUNCIATION Indicates when the unit has been selected to the Emergency Mode which inhibits RMU tuning capabilit...

Page 2317: ...on decimal digits in steps of 1 MHz for both VHF and VOR LOC 11 NORMAL EMERGENCY MODE SELECTOR KNOB BUTTON When knob rotated clockwise selects normal Mode When knob rotated counterclockwise selects Em...

Page 2318: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 13 Page 4 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2319: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 13 Page 5 Code 01 TUNING BACKUP CONTROL HEAD...

Page 2320: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 13 Page 6 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIOANLLY...

Page 2321: ...gen Masks and audio output selection between Speakers and Headphones Other features are the capability to filter the NDB VOR audio signals attenuating morse code or voice signals Finally Normal Mode a...

Page 2322: ...MANUAL 2 18 15 Page 2 Code 01 REVISION 36 AOM 145 1114 When power supply to the digital audio panel is resumed the normal mode of operation may be reestablished by selecting any other MICROPHONE butto...

Page 2323: ...PASSENGER BUTTON When pressed enables the crew to make the speech to the passenger cabin while simultaneously deselecting the previously selected COM transmitter 4 EMERGENCY BUTTON When pressed in ca...

Page 2324: ...above a certain threshold setting the audio will be re enabled 5 seconds after the audio level descends below that threshold setting If the mute function was selected when the marker beacon audio leve...

Page 2325: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 36 2 18 15 Page 5 Code 01 AOM 145 1114 DIGITAL AUDIO PANEL...

Page 2326: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 15 Page 6 Code 01 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 2327: ...through Passenger Address System Releasing this button it returns to the HOT position and VHF HF or passenger cabin transmissions will be interrupted NOTE For VHF transmissions a continuous command o...

Page 2328: ...age 2 Code 01 REVISION 19 GLARESHIELD COMMUNICATION SWITCH PTT 1 GLARESHIELD MIC PTT BUTTON When pressed allows VHF and HF transmission and speech to passengers through the Passenger Address System Re...

Page 2329: ...001 2 18 20 Page 3 Code 01 CAPTAIN AND COPILOT HAND MICROPHONE 1 HAND MIC PTT BUTTON When pressed allows VHF and HF transmission and speech to passengers through the Passenger Address System Releasing...

Page 2330: ...18 20 Page 4 Code 01 JUNE 28 2002 CAPTAIN AND COPILOT JACK PANELS 1 CAPTAIN AND COPILOT JACKS Allows plugging in the headphone the boom microphone and the hand microphone 2 HEADSET ANR Allows plugging...

Page 2331: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION JUNE 28 2002 2 18 20 Page 5 Code 01 CAPTAIN AND COPILOT JACK PANELS...

Page 2332: ...omentary position When pressed allows VHF and HF transmissions and speech to passengers through the passenger address system Releasing this button it returns to the OFF position and transmissions will...

Page 2333: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION JUNE 28 2002 2 18 20 Page 7 Code 01 OBSERVER JACK PANEL...

Page 2334: ...ATION FRONT AND REAR RAMP PANELS 1 COCKPIT CALL BUTTON momentary action When pressed generates a tone in the headphones and cockpit speakers 2 MICROPHONE HEADPHONE JACK Allows ramp crew to plug in a h...

Page 2335: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 20 Page 9 Code 01 FRONT AND REAR RAMP PANELS...

Page 2336: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 20 Page 10 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2337: ...mitted The upper sideband USB is the sum of the carrier frequency and the voice while the lower sideband LSB is the difference between the two The disadvantages of AM are that it occupies a wide spect...

Page 2338: ...ration means that the transmission and reception frequencies are the same An example of simplex operation would be communications with a control tower using a VHF COMM transceiver Half duplex means tr...

Page 2339: ...nter the frequency Use the four frequency select knobs to enter the desired frequency in the FREQ kHz display 3 Select the transmission mode Pull out and rotate the left inner PULL MODE knob in either...

Page 2340: ...CHAN FREQ switch to the CHAN position 2 Rotate the left outer channel select knob until user channel 1 or 40 appears on the right side of the CHAN display Use the right outer channel select knob to se...

Page 2341: ...only operation Receive only channels are used to listen to frequency standards W W V for example time weather Omega status and geophysical alert broadcasts HALF DUPLEX CHANNEL PROGRAMMING PROCEDURE 1...

Page 2342: ...ogrammed receive frequency At this point you have approximately 20 seconds to begin entering the desired transmit frequency If no changes are made during the next 20 seconds the currently displayed tr...

Page 2343: ...e of operation are entered The programming sequence is then terminated without entering a transmit frequency Program sequence can be terminated in any one of the three ways By momentarily keying the P...

Page 2344: ...ntarily key the PTT to initiate the antenna coupler tuning cycle A steady 1000 Hz tone will be heard in the headset or speaker while the antenna coupler is tuning Approximately 1 second after completi...

Page 2345: ...OBS Knob functions when selecting a discrete frequency FREQUENCY SELECT KNOB KNOB FUNCTION Left outer Selects the MHz digits 2 through 29 in the FREQ kHz display Left inner pushed in Selects the 100 k...

Page 2346: ...e of the CHAN display the left two or three digits are blanked Left inner pushed in or pulled out No effect on user channels Right outer With user channel 1 displayed clockwise rotation of this knob w...

Page 2347: ...TU band 22 MHz and user programmed channel number 1 and between the lowest ITU band 4 MHz and user programmed channel number 40 Left inner pushed in No effect on ITU channels Left inner pulled out Rot...

Page 2348: ...TROL This knob is adjusted to mute undesired background noise The noise proper setting is made by rotating the S squelch knob clockwise from TST test position until background noise can be heard and b...

Page 2349: ...ero shift position From this position the CLAR knob is adjusted clockwise or counterclockwise for the best clarity or the most natural sound of the signal being received NOTE When the audio quality of...

Page 2350: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 21 Page 14 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2351: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 21 Page 15 Code 01 CTL 230 HF CONTROL PANEL...

Page 2352: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 21 Page 16 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2353: ...nd below the carrier are generated and transmitted The upper sideband USB is the sum of the carrier frequency and the voice while the lower sideband LSB is the difference between the two The disadvant...

Page 2354: ...SEMI DUPLEX AND RECEIVE ONLY OPERATION Simplex operation means that the transmission and reception frequencies are the same An example of simplex operation would be communications with a control tower...

Page 2355: ...mentary press unlatches it and engages FREQ direct tune operation 2 Select the transmission mode Press the mode button to select the transmission mode USB LSB or AM 3 Enter the frequency Each digit in...

Page 2356: ...sure that the FREQ CHAN button is pressed in the CHAN position 2 Select the channel Rotate the small inner concentric knob to select the desired channel number 3 Tune the antenna Momentarily key the...

Page 2357: ...RE 1 Access channelized and program mode Apply power to the system by rotating the VOLUME V knob clockwise from the OFF position Make sure that the FREQ CHAN button is pressed in the CHAN position Act...

Page 2358: ...you program a channel for simplex operation both the receive and the transmit frequencies will be the same Programming a simplex channel is similar to programming a semi duplex channel except the STO...

Page 2359: ...ch cursor position 6 Store the information Push the STO store switch with a pointed object The information you have entered will be stored in the electronic memory After you push the STO button the TX...

Page 2360: ...hannel display will not show numbers 4 PHOTOCELL Automatically adjusts the display brightness 5 MODE SWITCH Selects transmission and reception mode Momentary depression cycles the KHF 950 from upper s...

Page 2361: ...off and controls volume Clockwise rotation past the first click turns the system on Further rotation increases audio level After turning on the system takes about two minutes to warm up Until then no...

Page 2362: ...de 02 JUNE 29 2001 To operate the clarifier pull the knob out and rotate the knob in either direction until the audio quality is optimized When the knob is pushed in the clarifier has no effect When v...

Page 2363: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION JUNE 29 2001 2 18 21 Page 11 Code 02 KCU 951 CONTROL PANEL...

Page 2364: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 21 Page 12 Code 02 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2365: ...with a single or DUAL KHF 1050 HF Communication System configuration Please refer to HF OPERATION RMU DISPLAYS RADIO PAGE HF Memory Page and HF Control Page in the section 2 18 11 to get instructions...

Page 2366: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 21 Page 2 Code 03 REVISION 33 INTENTIONALLY BLANK...

Page 2367: ...XFR MEM SWITCH This is a 3 position spring loaded toggle switch When held to the XFR position the preset frequency is transferred up to the active display and the equipment retunes The previously act...

Page 2368: ...stem At the completion of the self test program the display will return to its normal operation if no problem occurs In case of a detected failure diAG diagnostic letters will be displayed in the acti...

Page 2369: ...mory and TX transmit annunciators The MEM annunciator illuminates whenever a preset frequency is being displayed in the lower window The TX annunciator illuminates whenever the VHF 22A is transmitting...

Page 2370: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 22 Page 4 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2371: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 22 Page 5 Code 01 CTL 22 VHF CONTROL PANEL...

Page 2372: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 22 Page 6 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2373: ...rolled by the CTL 23C VHF Control Panel located at the main panel The Avionics Master DC Bus 1 supplies the third VHF Navigation Communications System with a protective 5A circuit breaker THIRD VHF NA...

Page 2374: ...displayed In case of any detected failure a different code will be displayed In this case record the code displayed to help the maintenance personnel to locate the problem SQ OFF Disables the VHF COM...

Page 2375: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 22 Page 3 Code 02 CTL 23C VHF CONTROL PANEL...

Page 2376: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 22 Page 4 Code 02 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2377: ...NDICATORS 1 ACTIVE FREQUENCY DISPLAY Displays the active frequency frequency to which the equipment is tuned and diagnostics messages 2 XFR MEM SWITCH This is a 3 position spring loaded toggle switch...

Page 2378: ...ostic code will remain displayed in the lower window The active and preset display intensity will flash modulating its brightness from minimum to maximum indicating self test in progress If no problem...

Page 2379: ...trols the display brightness 8 POWER AND MODE KNOB OFF Turns off the system ON Turns on the system 9 ANNUNCIATOR The NAV control contains MEM memory annunciator The MEM annunciator illuminates wheneve...

Page 2380: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 22 Page 4 Code 03 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2381: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 22 Page 5 Code 03 CTL 32 VHF CONTROL PANEL...

Page 2382: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 22 Page 6 Code 03 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2383: ...to the RMU The Avionics Master DC Bus 1A supplies the third VHF Communications System THIRD VHF COM NORMAL OPERATION In order to operate the third COM unit for voice communications it is necessary to...

Page 2384: ...same procedures applicable to regular COM units The announcements also will be the same Should any radio component fail or a disagreement occur between the frequency selection and the subsequent tran...

Page 2385: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 28 2002 2 18 22 Page 3 Code 04 RMU PAGE MENU...

Page 2386: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 22 Page 4 Code 04 MARCH 28 2002 RMU SYSTEM SELECT PAGE...

Page 2387: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 28 2002 2 18 22 Page 5 Code 04 RMU RADIO PAGE WITH THIRD VHF IN VOICE MODE...

Page 2388: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 22 Page 6 Code 04 MARCH 28 2002 RMU RADIO PAGE WITH THIRD VHF IN DATA MODE...

Page 2389: ...ne by transmitting a coded signal This coded signal will activate only one SELCAL unit to respond to that particular coded signal In this case a SELCAL voice message is activated through the Aural War...

Page 2390: ...OLS AND INDICATORS 1 SELCAL BUTTON A striped bar illuminates inside the associated button to alert the crew that communication is desired on VHF 2 or HF A SELCAL voice message sounds simultaneously Wh...

Page 2391: ...transmit routine information through voice transmission The system uses an assigned airborne VHF frequency to transmit and receive data from a ground station The ACARS is powered by 28 V DC from one o...

Page 2392: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 24 Page 2 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2393: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 24 Page 3 Code 01 ACARS SCHEMATIC...

Page 2394: ...Link Service Providers DSP The message is processed by the ACARS or when the message is addressed for a peripheral unit is passed on When an error free message has been received the ACARS generates a...

Page 2395: ...downlink buffer is full UNABLE TO SEND The transmission of a message has been manually initiated but the UniLink unit has determined that the message cannot be delivered to a ground system 2 LINE SELE...

Page 2396: ...in order of priority Activation when required is accomplished by pressing the line selecting button The ACARS Advisories in the order of priority are FAIL A new failure has been detected or has been r...

Page 2397: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 24 Page 7 Code 01 ACARS FMS CONTROL PANEL...

Page 2398: ...l character complement of printer and activates both external aural visual alert functions If button is pressed and held printer will successively print 40 60 80 column test patterns Otherwise each ti...

Page 2399: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 28 2002 2 18 24 Page 9 Code 01 PRINTER PANEL...

Page 2400: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 24 Page 10 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2401: ...veillance ADS The CMU is based on ARINC Characteristic 758 and can be upgraded by software download to an Aeronautical Telecommunications Network ATN router when protocols and application infrastructu...

Page 2402: ...oftware upgrades are released by the manufacturer The CMU is powered by the Avionic Switched DC Bus 1B The CMU interfaces with other airplane systems and equipment through the following equipments FMS...

Page 2403: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION OCTOBER 02 2001 2 18 24 Page 3 Code 02 CMU ARCHITETURE...

Page 2404: ...a queue for transmission If the aircraft is flying over a region or is grounded at an airport not covered by a DSP Data Link Service Provider reception or transmission of messages to or from a ground...

Page 2405: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION OCTOBER 02 2001 2 18 24 Page 5 Code 02 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2406: ...TROL DISPLAY UNIT CDU 1 LINE SELECT BUTTONS There are four line selection buttons on each side of the Control Display Unit CDU that provide selection of submodes within major modes when in an indexed...

Page 2407: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION OCTOBER 02 2001 2 18 24 Page 7 Code 02 CMU FMS CONTROL PANEL...

Page 2408: ...acter complement of printer and activates both external aural visual alert functions If button is pressed and held printer will successively print 40 60 80 column test patterns Otherwise each time the...

Page 2409: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 28 2002 2 18 24 Page 9 Code 02 PRINTER PANEL...

Page 2410: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 24 Page 10 Code 02 OCTOBER 02 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2411: ...o preserve the recorded data The CVR also incorporates an Underwater Locator Beacon ULB Powered by a dedicated battery the ULB starts transmitting an acoustic signal in the 37 5 kHz frequency once it...

Page 2412: ...y be heard from a headphone plugged to the CVR control panel jack confirming that the erase command was successful COCKPIT VOICE RECORDER CONTROLS AND INDICATORS 1 ERASE BUTTON Erases previously recor...

Page 2413: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 29 2 18 25 Page 3 Code 01 HONEYWELL COCKPIT VOICE RECORDER PANEL...

Page 2414: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 25 Page 4 Code 01 REVISION 29 L3 COCKPIT VOICE RECORDER PANEL...

Page 2415: ...and observer to flight attendant and vice versa through chime tone Call function from passenger to attendant through chime tone Chime tone for NO SMOKING and FASTEN SEAT BELTS signals Interface to boa...

Page 2416: ...ing the respective PTT HOT MIC switches The priority of the transmission through the system is the following captain copilot observer There are no chimes in this mode ATTENDANT TO PASSENGER MODE The A...

Page 2417: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 27 Page 3 Code 01 THIS PAGE S LEFT BLANK INTENTIONALLY...

Page 2418: ...Button except that it illuminates the Pilot Emergency Light labeled EMER PILOT on the Attendant s Call Panel A striped bar illuminates inside the button to indicate that it is pressed 3 BACKUP INTERPH...

Page 2419: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 27 Page 5 Code 01 INTERPHONE CONTROL UNIT...

Page 2420: ...ess the passengers PA or to communicate with the other attendant station ATTD or pilots PILOT and EMER PILOT The associated annunciator illuminates to indicate which button is pressed Annunciator colo...

Page 2421: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 31 2 18 27 Page 7 Code 01 ATTENDANT HANDSET...

Page 2422: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 27 Page 8 Code 01 REVISION 17 INTENTIONALLY BLANK...

Page 2423: ...ing the user to perform basic operations on the SATCOM system For advanced operation refer to the manufacturer s user manual SATCOM OPERATION When the Aero M system is powered up after a short pause t...

Page 2424: ...Region Satellite IOR Indian Ocean Region Satellite NOTE The Aero M system requires the user to determine the ocean region in which the aircraft is currently located The user must enter the user menu...

Page 2425: ...Access Code SNAC SNAC is a special country code that contacts the Network Coordinating Station for INMARSAT Aero M services and automatically routes the call to the satellite that Airborne Earth Stati...

Page 2426: ...hed the Yellow Ring Led will be illuminated Standard telephone calls Dial a telephone number by entering call prefixes country and area codes and number then press the key or the Toggle Hook key key 5...

Page 2427: ...to Navigate the user menu Place and receive calls Save and recall phonebook entries Configure system parameters View phone log Monitor system operations View system errors as they occur HANDSET KEYS...

Page 2428: ...selection 2 Toggles handset audio mode 3 Enable alpha mode Disable alpha mode Delete entry 4 Move one selection up Edit entry 5 Toggle hook 6 Move one selection down Mute 7 3 8 2 9 6 10 5 11 9 12 8 1...

Page 2429: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION JUNE 29 2001 2 18 28 Page 7 Code 01 HANDSET KEYS...

Page 2430: ...RIPTION 1 More entries above flag Indicates that additional entries are available above and can be displayed by pressing the Edit key 2 New AES messages flag A recorded MES message for the SDU SIM is...

Page 2431: ...icates that the handset has been locked and can only be accessed by entering a valid PIN code 9 2nd mode flag Indicates the 2nd key was pressed and the 2nd mode is active The next key pressed will per...

Page 2432: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 28 Page 10 Code 01 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2433: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION JUNE 29 2001 2 18 28 Page 11 Code 01 The figure below shows all the symbols found on the handset display HANDSET DISPLAY...

Page 2434: ...user of the following indications FIGURE NUMBER LED DESCRIPTION 1 Left Green Indicates power to handset 2 Right Green System is logged or is logging into the satellite network When on the antenna str...

Page 2435: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION JUNE 29 2001 2 18 28 Page 13 Code 01 HANDSET LED INDICATORS...

Page 2436: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 28 Page 14 Code 01 JUNE 29 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2437: ...Air Data Computers ADC 1 and ADC 2 The AHRS 1 and AHRS 2 receive true airspeed information from the ADC 1 and ADC 2 respectively to improve the precision of the computed navigation data Integrated Com...

Page 2438: ...ion information to the SPS Integrated Standby Instrument System ISIS the AHRS 1 provides heading information to the ISIS Windshear Detection And Escape Guidance System The AHRS 1 provides attitude rat...

Page 2439: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 30 Page 3 Code 01 AHRS SCHEMATIC...

Page 2440: ...the unit to measure the airplane angular motion The signals processed and generated by the IFOGs as well as the information of attitude heading and airplane axis accelerations are transmitted by the A...

Page 2441: ...ch and roll to produce a Schuler tuned erection loop for pitch and roll attitude and the flux valve is used as a continuous heading reference NOTE When switched from DG to SLVD Full Performance Mode t...

Page 2442: ...UAL 2 18 30 Page 6 Code 01 MARCH 30 2001 AH 800 EICAS MESSAGES TYPE MESSAGE MEANING CAUTION AHRS 1 2 OVERHEAT The associated AHRS computer is overheated ADVISORY AHRS 1 2 BASIC MODE The TAS input sign...

Page 2443: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 30 Page 7 Code 01 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2444: ...AHRS operates slaved to the flux valve which will provide a continuous heading reference 2 SLEWING SWITCH CW Allows selection in the clockwise direction of the desired heading to which the gyro will b...

Page 2445: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 17 2 18 30 Page 9 Code 01 AHRS CONTROL PANEL AH 800 VERSION ONLY...

Page 2446: ...hree axis inside of the AHRU which it uses to measure inertial motion The AHRU requires initialization data from the Flight Management System FMS and Air Data Computer ADC From inertial measurements i...

Page 2447: ...ALIGNMENT TIME minutes ALIGNMENT LATITUDE degrees Northern and Southern The airplane must remain stationary during alignment AHRS 1 2 ALN advisory message presented on the EICAS If the AHRU detects e...

Page 2448: ...ntry for its test calculations To pass the test the entered data must compare within 1 degree of the stored latitude longitude from the last power down from the NAV mode If the test fails the AHRS 1 2...

Page 2449: ...in the NAV mode and magnetic heading is not available For airplanes equipped with EICAS 18 and on the AH 900 must be initialized with magnetic heading In this case the operator needs to know the airpl...

Page 2450: ...iled AHRS 1 2 ATT MODE The associated AHRS is in the attitude mode AHRS 1 2 ALN The associated AHRS is in the alignment phase AHRS 1 2 ON BATT The associated AHRS is being powered by the airplane batt...

Page 2451: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 30 Page 15 Code 01 MAGNETIC VARIATION LATITUDE CUTOUTS AH 900 ONLY...

Page 2452: ...at zero degrees and 45 degrees LH and RH 3 ROLL POINTER Color White Provides the roll angular indication against the roll scale 4 EXCESSIVE PITCH CHEVRONS Color Red Marks 45 and 65 degrees pitch up an...

Page 2453: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 30 Page 17 Code 01 ELECTRONIC ATTITUDE DIRECTOR INDICATOR...

Page 2454: ...light Director couple arrow Low Bank limit arc Flight Director command bars Vertical Deviation scale pointer and label Radio Altitude digits label and box Marker beacons indicators Decision Height dig...

Page 2455: ...n the Full Compass or Arc formats selected via the Display Control Panel see section 2 18 40 Color white Range 360 degrees Resolution 5 degrees 2 HEADING LUBBER LINE FULL COMPASS FORMAT Color White Pr...

Page 2456: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 30 Page 20 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2457: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 30 Page 21 Code 01 EHSI FULL COMPASS AND ARC FORMATS...

Page 2458: ...by an ATT label displayed in the upper left portion of the attitude sphere in the same field of the ROL and PIT comparison monitors 2 ATTITUDE FAILURE DISPLAY Removal of the pitch scale and roll poin...

Page 2459: ...greater than 12 degrees The HDG threshold will be restored to 6 degrees if airplane roll is less than 5 degrees for 90 seconds Otherwise a 12 degrees HDG threshold will be maintained 6 HEADING FAILURE...

Page 2460: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 30 Page 24 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2461: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 30 Page 25 Code 01 AHRS FAIL INDICATION ON THE PFD BOTH AH 800 AND AH 900...

Page 2462: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 30 Page 26 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIOANALLY...

Page 2463: ...he airplane s systems and equipment is as follows Air Data Computers ADC 1 and ADC 2 The IRS 1 and IRS 2 receive altitude altitude rate and true airspeed information from the ADC 1 and ADC 2 respectiv...

Page 2464: ...S The IRS 1 provides heading information to the ISIS Head Up Guidance System HGS The IRS 1 or the dedicated IRS provides acceleration speed attitude heading and wind information to the HGS Windshear D...

Page 2465: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 30 Page 3 Code 02 IRS INTERFACES WITH OTHER SYSTEMS...

Page 2466: ...Selector Unit will illuminate Airplanes equipped with EICAS 17 onwards will also present the IRS 1 2 ON BATT advisory message on the EICAS INERTIAL REFERENCE UNIT IRU The Inertial Reference Unit cont...

Page 2467: ...cts the alignment time The relationship between alignment time and latitude is shown in the chart below 0 5 10 15 20 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 ALIGNMENT TIME minutes ALIGNMENT L...

Page 2468: ...arison test on latitude and longitude immediately after each data has been entered To pass the test the entered data must compare within 1 degree of the stored latitude longitude from the last power d...

Page 2469: ...down mode as its initial present position and updates the present position based only on inertial data while it remains in the NAV mode The IRU algebraically adds computed magnetic variations from a m...

Page 2470: ...or 3 seconds to prevent inadvertent selection After that power continues for 10 to 15 seconds to transfer the last calculated latitude and longitude and other IRS parameters to its non volatile memory...

Page 2471: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 30 Page 9 Code 02 MAGNETIC VARIATION LATITUDE CUTOUTS...

Page 2472: ...goes out and an IRS 1 2 ALN advisory message disappears from the EICAS on airplanes equipped with EICAS 17 onwards If the MSU switch is set to ALIGN set the MSU switch to NAV when the NAV RDY annunci...

Page 2473: ...ry message disappears from the EICAS on airplanes equipped with EICAS 17 onwards Initialize the IRU with magnetic heading through the FMS CDU Update heading periodically through the FMS CDU When opera...

Page 2474: ...complete the alignment phase successfully IRS 1 2 FAIL The associated IRS has failed IRS 1 2 ALN The associated IRS is in the alignment phase or the IRU mode select switch is set at ALIGN position ADV...

Page 2475: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 30 Page 13 Code 02 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2476: ...the MSU switch is moved from another position to OFF there will be a delay of 3 seconds before the IRU starts the power down routine in order to prevent its inadvertent selection ALIGN once this mode...

Page 2477: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 30 Page 15 Code 02 IRS MODE SELECTOR UNIT...

Page 2478: ...at zero degrees and 45 degrees LH and RH 3 ROLL POINTER Color White Provides the roll angular indication against the roll scale 4 EXCESSIVE PITCH CHEVRONS Color Red Marks 45 and 65 degrees pitch up an...

Page 2479: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 30 Page 17 Code 02 ELECTRONIC ATTITUDE DIRECTOR INDICATOR...

Page 2480: ...ight Director couple arrow Low Bank limit arc Flight Director command bars Vertical Deviation scale pointer and label Radio Altitude digits label and box Marker beacons indicators Decision Height digi...

Page 2481: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 30 Page 19 Code 02 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2482: ...n the Full Compass or Arc formats selected via the Display Control Panel see section 2 18 40 Color white Range 360 degrees Resolution 5 degrees 2 HEADING LUBBER LINE FULL COMPASS FORMAT Color White Pr...

Page 2483: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 30 Page 21 Code 02 EHSI FULL COMPASS AND ARC FORMATS...

Page 2484: ...tude sphere in the same field of the ROL and PIT comparison monitors 2 ATTITUDE FAILURE DISPLAY Removal of the pitch scale and roll pointer Coloring the attitude sphere overall blue A red ATT FAIL lab...

Page 2485: ...to 6 degrees if the airplane roll is less than 5 degrees for 90 seconds Otherwise a 12 degrees HDG threshold will be maintained 6 HEADING FAILURE DISPLAY Digital heading bug symbol is removed and a r...

Page 2486: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 30 Page 24 Code 02 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2487: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 30 Page 25 Code 02 IRS FAIL INDICATION ON THE PFD...

Page 2488: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 30 Page 26 Code 02 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2489: ...ADC 1 and 2 The GPS receives satellite data through the passive GPS antenna processing and blending collected data with ADC data and sends the resulting information to the FMS computer AHRS IRS 1 and...

Page 2490: ...perating modes for proper FMS operation The EMB 145 should have two types of FMZ 2000 CDU installed CD 810 or CD 820 In dual FMS configuration the intermix operation is not recommended The CD 810 CDU...

Page 2491: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 18 2 18 35 Page 3 Code 01 FMS SCHEMATIC...

Page 2492: ...or when other navaid are not available If all position sensors and radios are lost the FMS shifts to Degrade Mode DGRAD and in approximately 2 minutes it enters the Dead Reckoning Mode DR In this mode...

Page 2493: ...age of navaids airways departure procedures approach procedures Standard Terminal Arrival Routes STARs airports and runways This information is updated every 28 days The database can also store up to...

Page 2494: ...ough the prompt command available in the last page of the ACTIVE FLT PLAN pages Waypoints defined by the pilot created flight plans and radio tuning are automatically transferred to the cross side FMS...

Page 2495: ...he FMS cannot guarantee the position accuracy for the present phase of the flight MSG White Illuminates when there is a message advisory or alert on the scratchpad The annunciator turns off when the m...

Page 2496: ...chpad The brightness can be adjusted so that during daylight conditions the display cannot be seen 4 MODE BUTTONS PERF Displays the performance pages NAV Displays the NAV index pages FPL It may be use...

Page 2497: ...DEO NOT AVAILABLE GRAPHIC GRAPHIC NOT AVAILABLE ATC ATC NOT AVAILABLE BACK BACK COMPLETE FN FN NOT AVAILABLE 7 SCRATCHPAD It is the working area located on the bottom line of the display where the pil...

Page 2498: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 35 Page 10 Code 01 JUNE 28 2002 FMZ 2000 FMS CD 810 CONTROL PANEL...

Page 2499: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION JUNE 28 2002 2 18 35 Page 11 Code 01 FMZ 2000 FMS CD 820 CONTROL PANEL...

Page 2500: ...gnator Symbol movement on the MFD FMS flight plan JOYSTICK OPERATION On power up the designator is co located with the present flight plan waypoint position If MAP mode is selected moving the joystick...

Page 2501: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 35 Page 13 Code 01 JOYSTICK CONTROLLER...

Page 2502: ...NTER ENT button The latitude and longitude coordinates of the designator are transmitted to the selected FMS scratchpad as a requested waypoint JOYSTICK MENU BUTTONS FUNCTION AT PLAN MODE SKIP SKP but...

Page 2503: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 29 2 18 35 Page 15 Code 01 MFD JOYSTICK MENU...

Page 2504: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 35 Page 16 Code 01 REVISION 23 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2505: ...DC 1 and 2 The GPS receives satellite data through the passive GPS antenna processing and blending collected data with ADC data and sends the resulting information to the FMS computer AHRS IRS 1 and 2...

Page 2506: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 35 Page 2 Code 02 REVISION 17 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2507: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 18 2 18 35 Page 3 Code 02 FMS SCHEMATIC...

Page 2508: ...enter into DME DME mode Two different scenarios can explain the GPS sensor being deselected 1 In a multi sensor configuration the GPS position is monitored the same as DME DME IRS and Loran C sensor i...

Page 2509: ...tegrity monitor is defined for three phases of flight each with a specified Alarm Limit and Time to Alarm as showed in the table below Phase of Flight Alarm Limit Time to Alarm Enroute 2 0 NM 27 secon...

Page 2510: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 35 Page 4B Code 02 REVISION 35 CDU SCREEN...

Page 2511: ...The dual FMS configuration may operate with dual IRS and dual GPS providing four long range navigation sensors In this configuration on side FMS outputs and flight plan information are available to t...

Page 2512: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 35 Page 4D Code 02 REVISION 35 INTENTIONALLY BLANK...

Page 2513: ...navigation computer can be programmed by the operator to automatically fly different types of holding patterns DATA BASE The database contains worldwide coverage of navaids airways departure procedur...

Page 2514: ...a new message is generated WPT Yellow Indication concerning Lateral waypoint alert when steady A flashing indication announces a Vertical waypoint flight plan angle alert SXTK Amber Indication concern...

Page 2515: ...e PERF 1 1 provides a synopsis of pertinent in flight performance information DATA Provides information concerning the FMS NAV Data Base and operating attached sensors as well as their status FUEL Dis...

Page 2516: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 35 Page 8 Code 02 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2517: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 35 Page 9 Code 02 UNS 1K FMS CONTROL PANEL...

Page 2518: ...gnator Symbol movement on the MFD FMS flight plan JOYSTICK OPERATION On power up the designator is co located with the present flight plan waypoint position If MAP mode is selected moving the joystick...

Page 2519: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 19 2 18 35 Page 11 Code 02 JOYSTICK CONTROLLER...

Page 2520: ...ich the designator line is extended and the designator line is removed from the display ENTER ENT button Confirms the waypoint desired location JOYSTICK MENU BUTTONS FUNCTION AT PLAN MODE SKIP SKP but...

Page 2521: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 29 2 18 35 Page 13 Code 02 MFD JOYSTICK MENU...

Page 2522: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 35 Page 14 Code 02 REVISION 23 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2523: ...cator EHSI The EHSI navigation sources as well as the display format Full Compass or Arc may be selected by the crew via the Display Control Panel DCP Several other navigation data are also presented...

Page 2524: ...nce of control RESET ELAPSED TIME STOP REPEAT 4 NAVIGATION SOURCES SELECTOR BUTTON Provides the selection of the VHF NAV VOR ILS and MLS as navigation source for the EHSI If the VHF NAV is already sel...

Page 2525: ...ctive ADF as source for the associated bearing pointer FMS Selects the FMS as source for the associated bearing pointer 7 DECISION HEIGHT SETTING AND IC 600 TEST KNOB Provides the Radio Altimeter RA d...

Page 2526: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 40 Page 4 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2527: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 40 Page 5 Code 01 DISPLAYS CONTROL PANEL...

Page 2528: ...e for the on side EHSI and for the on side MFD MAP Pressing the FMS Button once again will restore the normal operation FMS 1 information presented on the PFD 1 and MFD 1 and FMS 2 information present...

Page 2529: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 40 Page 7 Code 01 CROSS SIDE FMS SOURCE SELECTION ON THE MFD...

Page 2530: ...to LOC is active 2 MARKER BEACON DISPLAY Color O label cyan M label amber I label white Box white An O an M or an I flashing annunciation is displayed when the outer marker the middle marker or the in...

Page 2531: ...ution 1 KIAS TIME TO GO DISPLAY Color Digits the same of the NAV source color TTG label white Range 0 to 399 min Resolution 1 minute ELAPSED TIME Color Digits green ET label green Range 00 00 to 09 59...

Page 2532: ...ers Source annunciation will be retained on the PFD even in case of an invalid bearing signal 9 DME HOLDING AND DISTANCE ANNUNCIATION Color Digits green NM label white H label amber Range Short Range...

Page 2533: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 40 Page 11 Code 01 ADF VHF NAV AND DME INDICATIONS ON THE PFD EHSI IN FULL COMPASS FORMAT...

Page 2534: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 40 Page 12 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2535: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 40 Page 13 Code 01 ADF VHF NAV AND DME INDICATIONS ON THE PFD EHSI IN ARC FORMAT...

Page 2536: ...he pointer will be magenta otherwise it will be amber 3 MESSAGE ANNUNCIATION Label MSG Color Amber The MSG is displayed when a message is available on the FMS Panel 4 GROUND SPEED TIME TO GO DATA Labe...

Page 2537: ...onfiguration there will be an indication if FMS 1 or 2 is being used 10 WIND VECTOR DISPLAY Color Magenta A single vector shows the direction of the wind relative to the airplane symbol The digits ind...

Page 2538: ...indicator sensitivity and FMS tracking gains are increased The TERM annunciator is displayed when the airplane enters in the terminal area or when the lateral deviation scaling has been set to the enr...

Page 2539: ...ach FMS is the navigation source for the respective side the CRS and DTK labels will be magenta Otherwise they will be amber The readouts will have the same color as the CRS and DTK annunciations DTK...

Page 2540: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 40 Page 18 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2541: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 40 Page 19 Code 01 FMS INDICATION ON THE PFD...

Page 2542: ...yed as a four pointed star at the geographical locations referenced to the current present position where the selected transitions of the flight plan occur A maximum of 10 Waypoints can be displayed i...

Page 2543: ...gits indicate the wind intensity in knots 10 DESIGNATOR SYMBOL Color Same color of the Waypoint If the Designator is co located with a connected Waypoint Cyan If it is not connected The Designator sym...

Page 2544: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 40 Page 22 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2545: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION AUGUST 24 2001 2 18 40 Page 23 Code 01 FMS INDICATION ON THE MFD...

Page 2546: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 40 Page 24 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2547: ...th of the airplane The system provides the flight crew with visual indications regarding turbulence content P 880 only and rainfall intensity Precipitation intensity level is displayed in four bright...

Page 2548: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 45 Page 2 Code 01 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 2549: ...data are displayed on PFDs and MFDs radar mode field The weather radar system run on 28 V DC powered by one of the Avionics Switched DC Buses Should a power supply failure occur the weather radar sys...

Page 2550: ...ith an ideal raindrop diameter The weather radar can see rain wet snow wet hail and dry hail depending on its diameter The radar can not see water vapor ice crystals and small dry hail At higher altit...

Page 2551: ...REVISION 38 2 18 45 Page 5 Code 01 AOM 145 1114 EM145AOM182107A DGN WHAT THE WEATHER RADAR SEES REFLECTIVE LEVEL WET HAIL GOOD RAIN GOOD WET SNOW GOOD DRY HAIL POOR DRY SNOW VERY POOR WATER VAPOR NO...

Page 2552: ...d standby FSBY if the airplane is on the ground GROUND OPERATION PRECAUTIONS If the radar system is to be operated in any mode other than standby or forced standby while the airplane is on the ground...

Page 2553: ...combined with the END OF LIST page RADAR FAIL indicates a radar fault During the weather radar test several fault messages may be presented to the crew The POC Power On Counter aside recording an exi...

Page 2554: ...OVERRIDEN ON THE GROUND AND ANY RADAR ACTIVE MODE IS SELECTED THE TRANSMITTER IS TURNED ON THE RADAR MUST NOT BE OPERATED UNDER THIS CONDITION WHILE REFUELING NEAR FUEL SPILLS OR PEOPLE WEATHER DETEC...

Page 2555: ...imum gain value and weather targets can no longer be calibrated The point where red level weather target calibration is no longer possible is highlighted by changing the background field from black to...

Page 2556: ...altered to provide equalization of ground target reflection versus range The selection of calibrated GAIN will generally provide the desired mapping display If required variable gain may be used to r...

Page 2557: ...mile range When selected target alert monitors for red or magenta weather beyond the selected range and 7 5 on either side of the airplane s heading If such weather is detected within the monitored a...

Page 2558: ...is disabled Variable VAR When the GAIN knob is pulled out the system enters the variable gain mode Variable gain is used for additional weather analysis and for ground mapping In the WX mode variable...

Page 2559: ...table below gives the approximate tilt settings for minimal ground target display for different altitudes and ranges If the altitude changes or a different range is selected adjust the tilt control a...

Page 2560: ...TUDE ft LINE OF SIGHT nm 5 10 25 50 100 200 300 40000 35000 30000 25000 20000 15000 10000 5000 4000 3000 2000 1000 246 230 213 195 174 151 123 87 78 67 55 39 5 4 2 0 2 6 1 0 1 2 3 8 6 4 2 0 12 10 3 3...

Page 2561: ...he next figure helps to visualize the relationship between tilt angle flight altitude and selected range It shows the distance above and below airplane altitude that is illuminated by the radar during...

Page 2562: ...000 0 0 25 50 75 100 ZERO TILT 10500 ft 10500 ft 20000 ft 20000 ft CENTER OF RADAR BEAM 41800 ft 41800 ft RANGE nm ELEVATION ft 40000 30000 20000 10000 0 0 10 20 30 40 50 60 70 80 RANGE nm 10500 ft 10...

Page 2563: ...management demands that tilt be changed continuously even in airplanes equipped with ACT SLAVE SLV DUAL CONTROL PANEL ONLY For airplanes equipped with dual weather radar control panels one controller...

Page 2564: ...of grease or dirt over the radome s surface also impairs radar transmission These should be reported immediately to maintenance personnel for cleaning or corrective action Electrostatic Discharges St...

Page 2565: ...between MFD bezel 1 or 2 the weather radar system behavior can be summarized as follows For airplanes equipped with Single Radar Controller Configuration WX Controller Adjustment through MFD 1 Indicat...

Page 2566: ...Controller 2 RH side MFD 1 Indication MFD 2 Indication 1 STDBY OFF 2 STDBY WX 3 WX OFF 4 WX STDBY Terrain map image and ARC Range setting work independently through MFD Bezel 1 and 2 5 OFF WX 6 OFF S...

Page 2567: ...Model Only Alternate pressings turns on or off the radar s turbulence detection function Function can be used only in WX or RCT mode with selected range of 50 NM or less 3 STABILIZATION FUNCTION BUTTO...

Page 2568: ...barometric altitude and or selected range 8 RADAR MODES CONTROL KNOB OFF Turns off the weather radar SBY Selects the weather radar standby operating mode WX Selects the weather radar detection operat...

Page 2569: ...STAL TRB STB TGT SECT MAX MIN WX SBY OFF RCT GAIN RADAR TILT GMAP FP TST PULL VAR PULL ACT RCT STAB TGT SECT MAX MIN WX SBY OFF GAIN RADAR TILT GMAP FP TST PULL VAR 15 0 P 880 MODEL P 660 MODEL NOTE S...

Page 2570: ...l be highlighted by a white box The weather radar can only be selected for display in map format If the weather radar is selected with plan format already selected on the MFD it will force the display...

Page 2571: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 38 2 18 45 Page 25 Code 01 AOM 145 1114 EM145AOM182032A DGN 1 PLAN RNG M P WX MAP MFD 2 MFD BEZEL PANEL...

Page 2572: ...en low intensity reflection 3 WEATHER RADAR TURBULENCE INDICATION P 880 Model Only Indicates an area of detected turbulence Color white 4 WEATHER RADAR REACT INDICATION Indicates an area where radar r...

Page 2573: ...X ON and selected for display WX AMBER Invalid WX control bus TX GREEN WX is transmitting but not selected for display or in STBY or FSTBY TX AMBER WX is transmitting and weight on wheels indicates on...

Page 2574: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 45 Page 28 Code 01 REVISION 38 AOM 145 1114 EM145AOM182033A DGN PFD 33 N 3 WX 5O 3 O TGT 1 3 2 4 8 6 7 5 WEATHER RADAR DISPLAY ON PFD...

Page 2575: ...MANUAL NAVIGATION AND COMMUNICATION REVISION 38 2 18 45 Page 29 Code 01 AOM 145 1114 EM145AOM182034A DGN MFD 25 TX TGT STAB 15 N 3 3 O 6 33 PLAB1 PBDO1 LLO1 KDVT PLAB2 5O 5O O 1 2 3 4 5 6 8 7 WEATHER...

Page 2576: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 45 Page 30 Code 01 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 2577: ...und the aircraft and to give the operator a visual display of its position and rate of occurrence on the MFDs The Lightning Sensor System is inhibited on the ground and during HF transmission HF PTT b...

Page 2578: ...lied to the system a self test is automatically performed and in the event of failure an amber LX F will be displayed on the MFDs The LSS also performs self calibration each time the system is turned...

Page 2579: ...magenta lightning symbols near the outer range marks When operating the LSS with the Radar in STBY Mode 360 of data is displayed A green LX will be displayed on normal operation Lightning Sensor Displ...

Page 2580: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 50 Page 4 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2581: ...AND INDICATORS 1 LIGHTNING SENSOR SYSTEM CONTROL KNOB OFF Turns off the Lightning Sensor System SBY Selects the Lightning Sensor System Standby Mode LX Selects the Lightning Sensor System Detection O...

Page 2582: ...ile diameter area of lightning activity with 3 strikes every 2 minutes 4 LEVEL 4 ALERT LIGHTNING ACTIVITY INDICATION Color Magenta Indicates only the bearing of lightning activity without determining...

Page 2583: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION MARCH 30 2001 2 18 50 Page 7 Code 01 LIGHTNING SENSOR SYSTEM DISPLAY ON MFD...

Page 2584: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 50 Page 8 Code 01 MARCH 30 2001 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2585: ...nd speed and direction flight path and other information to the pilot in symbolic format that is superimposed on the pilot s view The HGS also provides guidance cues for low visibility takeoff and CAT...

Page 2586: ...ers for ILS data plus a third ILS 3 to serve as a monitor Two Radar Altimeters RA for altitude above ground data and decision height selection Flight Guidance System FGS for Flight Director command si...

Page 2587: ...S DATA WINDSHEAR GROUND PROXIMITY GROUND TRACK GROUND TRACK CHANNEL 1 CHANNEL 2 TCAS RESOLUTION HGS COMPUTER TCAS STALL PROTECTION COMPUTER GPS 1 GPWS FMS 1 FMS DATA AIR DATA ADC 2 AIR DATA ADC 1 DAU...

Page 2588: ...operation It also provides an indication of the system s ability to provide Cat IIIa guidance Powered by the DC Bus 1 the HCP is located in the center pedestal and is available to both pilots Display...

Page 2589: ...TION REVISION 39 2 18 75 Page 5 Code 01 AOM 145 1114 EM145AOM182054A DGN HGS MESSAGES F O S PFD OVERHEAD UNIT COMBINER MODE STBY RWY G S CLR DIM BRT FAULT TEST ENTER 1 2 3 4 5 6 7 8 9 0 H G S PRI IMC...

Page 2590: ...d windscreen The Combiner has three positions stowed operating and breakaway Stowed when the HGS is not in use the Combiner may be stowed out of the pilot s field of view To stow the Combiner press th...

Page 2591: ...ying The Primary mode display includes the following symbolic information Airplane Reference boresight symbol Pitch scale and horizon relative to boresight Roll scale and horizon relative to boresight...

Page 2592: ...l visual references AIII MODE The HGS AIII mode is designed for precision manual ILS approach and landing operations to CAT IIIa minimums Additionally the AIII mode can be used for CAT II approaches D...

Page 2593: ...BIT faults present Radio altitude greater than 500 ft Glideslope set between 2 50 and 3 00 AIII mode becomes available for selection when the above listed conditions are satisfied and the Approach On...

Page 2594: ...annunciation on the Combiner display and on the F O s PFD The flare maneuver is designed to transition the airplane from approach attitude to touchdown attitude while maintaining positioning and perfo...

Page 2595: ...dance is displayed in IMC mode as long as the flight director pitch and roll commands are valid Once on the ground the Ground Localizer Scale and Index is displayed as in the Primary mode VMC MODE The...

Page 2596: ...f and recovery from unusual attitude situations The Unusual Attitude UA symbology is automatically activated or deactivated based upon the attitude of the airplane When activated the UA display replac...

Page 2597: ...Flight Path is positioned within the safe zone Preventive Advisories are displayed on the HGS as a double line bracket with two angled lines extending from the corners on the unsafe side of the brack...

Page 2598: ...ABILITY in the HGS TEST MENU displayed on the Combiner In case of no AIII capability detected the faults will be displayed on the Combiner If the system is capable of performing the AIII mode AIII is...

Page 2599: ...TRY SELECTOR BUTTON Activates the Glideslope Data Entry mode to enter the glideslope angle 8 FAULT ANNUNCIATOR LAMP Indicates a fault in the critical processing path detected by the HGS built in test...

Page 2600: ...s mode Rotating the knob clockwise increases display intensity Rotating counterclockwise decreases display intensity In this mode the intensity remains constant at the level selected by the pilot Pull...

Page 2601: ...for invalid sensor statuses and miscompares between certain similar parameters These are generally indicated by boxed annunciations for the affected parameters and in the case of a failure the remova...

Page 2602: ...T Indicates IRS AHRS2 Pitch or Roll miscompare or a AHRS1 AHRS2 Attitude miscompare Indicated by boxed PIT ROL or ATT characters respectively beneath the left side of the roll scale ATT FAIL Indicates...

Page 2603: ...a low visibility takeoff Indicated by boxed characters and removal of the ground localizer pointer LOC ILS Indicates Localizer miscompare Indicated by boxed characters in the lower left portion of the...

Page 2604: ...ombiner VNAV Indicates Vertical Deviation failure Indicated by boxed characters VNAV Vertical Navigation replacing the vertical deviation scale VS Indicates Vertical Speed failure Indicated by boxed c...

Page 2605: ...ctor panel and top and bottom antennas The transponder is capable of receiving transmitting signals through any one antenna thus inhibiting the shadow effect caused by the airplane structure while man...

Page 2606: ...s DAP are transmitted automatically to be used by the ground Air Traffic Management Magnetic Heading Indicated Airspeed and or Mach Number Vertical Rate Roll Angle True Airspeed True Track Angle Groun...

Page 2607: ...AIRPLANE OPERATIONS MANUAL NAVIGATION AND COMMUNICATION REVISION 38 2 18 80 Page 3 Code 01 AOM 145 1114 1 2 EM145AOM182092A DGN SELECTOR XPDR IFF TRANSPONDER SELECTOR KNOB...

Page 2608: ...ay and keypad entry mode MODE S Selecting S with the DPL SEL knob enables the Mode S display and keypad entry mode FLIGHT ID Selecting FLT ID with the DPL SEL knob enables FLIGHT ID display and keypad...

Page 2609: ...position and pressing the TEST push button In addition the TCAS is tested when the test is performed Pressing the TEST push button the Mode S IFF control panel starts a lamp test turning all front pan...

Page 2610: ...ent modes of operation and allows for selection of TCAS functions OFF Disables the Modes 3 A C and S MODE 3 A When Mode 3 A is enabled replies to Mode 3 A interrogations and Mode C framing pulses are...

Page 2611: ...eration mode supplying full TCAS coverage 8 CODE ENTRY KEYPAD There are 12 push button keys in the keypad 9 TCAS HORIZONTAL RANGE ROTARY KNOB The TCAS range control allows the pilot to select traffic...

Page 2612: ...ground The SPI supplies the ground station with more positive identification of airplane position This is typically activated upon verbal command of the Air Traffic Controller The IDNT control is a mo...

Page 2613: ...45AOM182094A DGN DPL SEL 2 3A S STAT FLT 1 ID MODE 4 ON AUDIO M4 LT OFF OFF ZERO HOLD B A ABC JKL MNO DEF 1 2 4 5 6 3 GHI PQR 9 8 7 STU VWX YZ ENT 0 CLR IDNT 1 2 1 2 OFF MOD 1 2 SEL REPLY MODE TCAS C...

Page 2614: ...NAVIGATION AND COMMUNICATION AIRPLANE OPERATIONS MANUAL 2 18 80 Page 10 Code 01 REVISION 38 AOM 145 1114 INTENTIONALLY BLANK...

Page 2615: ...10 04 LNAV Mode 2 19 10 05 Vertical Modes 2 19 10 06 Pitch Hold Mode 2 19 10 06 Altitude Hold Mode ALT 2 19 10 06 Altitude Preselect Mode ASEL 2 19 10 07 Flight Level Change Mode FLC 2 19 10 07 Speed...

Page 2616: ...e 01 REVISION 36 AOM 145 1114 Category II Approach 2 19 20 01 Category II Conditions 2 19 20 01 Localizer Excessive Deviation Warning 2 19 20 02 Glideslope Excessive Deviation Warning 2 19 20 02 Contr...

Page 2617: ...19 05 Page 1 Code 01 GENERAL The Primus 1000 P 1000 Automatic Flight Control System AFCS is a fully integrated fail passive three axis flight control system which incorporates lateral and vertical gui...

Page 2618: ...remote selection of course heading vertical speed target indicated airspeed target Mach targets and preselected altitude PITCH AND TURN CONTROLLER PC 400 Consists of a panel with a Turn Control Knob a...

Page 2619: ...tion localizer deviation selected decision height selected course packed discrete and selected terrain range ELECTRONIC FLIGHT INSTRUMENT SYSTEM EFIS present information to the flight crew Consists of...

Page 2620: ...ng attitude heading air data radio altimeter navigation and pilot inputs These attitude commands are sent to the PFD for pilot display to the autopilot for automatic airplane control and to the autopi...

Page 2621: ...AIRPLANE OPERATIONS MANUAL AUTOPILOT JUNE 28 2002 2 19 05 Page 5 Code 01 AUTOFLIGHT SYSTEM SCHEMATIC...

Page 2622: ...AUTOPILOT AIRPLANE OPERATIONS MANUAL 2 19 05 Page 6 Code 01 JUNE 28 2002 THIS PAGE IS LEFT BLANK INTENTIONALLY...

Page 2623: ...this mode is selected the heading reference is established one second after the system detects a bank angle of less than 6 A bank angle command of 0 is used wings level until the heading reference is...

Page 2624: ...t is disengaged and the Turn Control Knob is out of detent the TKNB label is displayed in the PFD and the autopilot engagement is inhibited WINGS LEVEL SUBMODE Airplanes equipped with EICAS 16 and on...

Page 2625: ...ive but remains selected if Heading Select mode is deactivated being reactivated and annunciated if Heading mode is selected again The Low Bank mode is automatically selected when climbing above 25000...

Page 2626: ...VAPP mode only on the final approach segment Therefore the outbound segment should be flown using some other mode This mode is selected by pressing the APR button on the Flight Guidance Controller wi...

Page 2627: ...ted if any of the following conditions occur Pressing the NAV or APR buttons Selecting HDG mode Changing the displayed NAV source on the PFD Changing the displayed heading source on the PFD When the d...

Page 2628: ...so be considered as a lateral mode PITCH HOLD MODE The Pitch Hold mode is the default mode that controls the airplane when no other Flight Director mode is selected The Pitch Hold mode is synchronized...

Page 2629: ...ed with autopilot engaged ALTITUDE PRESELECT MODE ASEL The Altitude Preselect mode provides means for the system to climb or descend to a predetermined altitude and then level off and maintain the pre...

Page 2630: ...urrent altitude and FLC is selected the FD provides a command to descend at a determined rate of descent The PFD will display the current IAS Mach or vertical speed bug as appropriate and the target s...

Page 2631: ...T VS FLC or SPD modes Glide slope capture When the air data is invalid Pressing the Go Around Button DESCENT RATE SCHEDULE For EICAS versions up to 13 The descent rate schedule is 2000 ft min For EICA...

Page 2632: ...TOPILOT AIRPLANE OPERATIONS MANUAL 2 19 10 Page 10 Code 01 REVISION 36 AOM 145 1114 CLIMB RATE SCHEDULE For climb rate schedule see the chart below EMB 145 All models except EMB 145 XR EMB 145 XR Mode...

Page 2633: ...mode and Glide Slope arm mode Speed Hold mode is automatically selected when the FLC button is pressed and the preselected altitude is above the current altitude Different Speed Target can be selecte...

Page 2634: ...lected by pressing the VS button on the Flight Guidance Controller or automatically when FLC button is pressed and the preselected altitude is below the current altitude This mode is annunciated on th...

Page 2635: ...ide slope deviation invalid for a period greater than 5 seconds Pressing the Go Around Button GO AROUND MODE The Go Around mode may be engaged only at radio altitudes below 2500 ft or below 15000 ft p...

Page 2636: ...Hold mode and synchronizes to the current attitude This submode does not couple to the autopilot which may be used after climbing above the airplane Minimum Engagement Height MEH A Pitch Limit Indicat...

Page 2637: ...f this speed can not be maintained altitude is held If 20 seconds after Go Around engagement the speed is higher than 170 KIAS In this case 170 KIAS is targeted replacing the pre selected speed target...

Page 2638: ...t is disengaged The voice message occurs at any altitude in case of intentional disengagement or due to an autopilot failure and may be canceled according to the following associated conditions Associ...

Page 2639: ...A roll mistrim condition exists LATERAL MODE OFF Inadvertent loss of the Lateral Flight Director mode VERTICALMODE OFF Inadvertent loss of the Vertical Flight Director mode YAW DAMPER FAIL Yaw Damper...

Page 2640: ...de 3 AUTOPILOT ENGAGE BUTTON Pressed once engages the autopilot and the yaw damper Pressed again disengages the autopilot only keeping the yaw damper engaged 4 VERTICAL MODE SELECTOR BUTTONS Select ve...

Page 2641: ...MPER ENGAGE BUTTON Pressed once engages only the Yaw Damper Pressed again disengages the yaw damper and the autopilot if it is engaged 9 AUTOPILOT COUPLE BUTTON Allows the pilot s or copilot s Flight...

Page 2642: ...AUTOPILOT AIRPLANE OPERATIONS MANUAL 2 19 15 Page 4 Code 01 REVISION 36 AOM 145 1114 FLIGHT GUIDANCE CONTROLLER...

Page 2643: ...ngaged and the Pitch Hold mode is selected Pitch control wheel operation is inhibited if any vertical mode except the Pitch Hold mode is selected in the Flight Director 2 TURN CONTROL KNOB Manually co...

Page 2644: ...AUTOPILOT AIRPLANE OPERATIONS MANUAL 2 19 15 Page 6 Code 01 REVISION 36 AOM 145 1114 PITCH AND TURN CONTROLLER...

Page 2645: ...rned to the previously selected lateral mode return to the lateral mode is filtered to prevent rapid maneuvers After glide slope capture in APR mode with the autopilot engaged if the TCS button is pre...

Page 2646: ...AUTOPILOT AIRPLANE OPERATIONS MANUAL 2 19 15 Page 8 Code 01 REVISION 36 AOM 145 1114 CONTROL WHEEL...

Page 2647: ...45 1114 THRUST LEVERS 1 GO AROUND BUTTON Selects the Go Around mode Takeoff submode Go Around Speed Target submode and Windshear mode The button also forces the Flight Director into either the Go Arou...

Page 2648: ...ELECTOR BUTTON OPTIONAL Provides the selection of the FMS as navigation source for the EHSI On airplanes equipped with dual FMS pressing the FMS Button for the second time selects the opposite FMS as...

Page 2649: ...00 TEST KNOB Provides the Radio Altimeter RA decision height setting When pressed on ground provides the IC 600 and RA test activation Refer to Section 2 4 Crew Awareness for further information on te...

Page 2650: ...AUTOPILOT AIRPLANE OPERATIONS MANUAL 2 19 15 Page 12 Code 01 REVISION 36 AOM 145 1114 DISPLAY CONTROLLER PANEL DG 550...

Page 2651: ...at a time The following messages may be displayed MESSAGE COLOR MEANING AP Autopilot engaged AP TEST Green Autopilot test mode is active immediately after power up TCS White TCS submode is engaged au...

Page 2652: ...red The mode annunciation is removed if the Flight Director fails 7 MODE TRANSITION ANNUNCIATOR Each transition is annunciated by a box around the mode that is being transitioned The box will highligh...

Page 2653: ...ector selected source or tuned frequency is different NOTE The command bar and airplane symbol may be presented in either V bar or cross bar formats depending on operator selection 11 SELECTED HEADING...

Page 2654: ...son monitor display is annunciated when both GS and LOC comparison monitors are displayed simultaneously 15 AOA INDICATION Color amber Indicates loss of PLI indication due to an invalid Stall Protecti...

Page 2655: ...S 26O WX 5O 3 5 FMS APP KDVT DR VOR1 ADF2 TGT 245KTS MAG2 HDG MSG TCAS TEST 3OOO 2OO RA 359 41O 12 5 ATT2 LOC SXTK FHDG RA CAS MSG M A M X S P D AP YD G S ASEL ADC2 SG2 VTA FMS A LOC 16 17 15 22O 2OO...

Page 2656: ...VS 26O WX 5O 3 5 FMS APP KDVT DR VOR1 ADF2 TGT 245KTS MAG2 HDG MSG TCAS TEST 3OOO 2OO RA 359 41O 12 5 ATT2 LOC SXTK FHDG RA CAS MSG M A M X S P D AP YD G S ASEL ADC2 SG2 VTA FMS A LOC 16 17 15 22O 2O...

Page 2657: ...N Color amber Indicates that a roll mistrim exists which may cause an abrupt roll command at the time the autopilot is disengaged Direction of arrow indicates the side the roll trim must be commanded...

Page 2658: ...AUTOPILOT AIRPLANE OPERATIONS MANUAL 2 19 15 Page 20 Code 01 REVISION 36 AOM 145 1114 INTENTIONALLY BLANK...

Page 2659: ...ing valid on both PFDs Glide slope and localizer deviation valid on both PFDs No reversions SG AHRS IRS or ADC modes selected on both PFDs Valid airspeed and barometric altitude on both PFDs No compar...

Page 2660: ...changed from green to amber The lateral deviation scale changing from white to amber and flashing with a duty cycle of 0 5 second on followed by a 0 5 second off NOTE The on side excessive deviation...

Page 2661: ...ANUAL AUTOPILOT REVISION 40 2 19 20 Page 3 Code 01 AOM 145 1114 CONTROLS AND INDICATORS PFD INDICATORS 1 CAT 2 ANNUNCIATION Indicates the Cat II condition Label CAT 2 Color Normal condition green Abno...

Page 2662: ...AUTOPILOT AIRPLANE OPERATIONS MANUAL 2 19 20 Page 4 Code 01 REVISION 40 AOM 145 1114 PFD INDICATORS...

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