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Copyright 2012 by EMBRAER S.A.. All rights reserved. This document shall not be copied or reproduced, whether inwhole or in part, in any form or by any means without the express written authorization of Embraer. The information,technical data, designs and drawings disclosed in this document are property information of Embraer or third parties

and shall not be used or disclosed to any third party without permission of Embraer.

EMBRAER 170/175/190/195

STANDARD OPERATING PROCEDURESMANUAL

EMBRAER S.A.

This manual is applicable to EMBRAER 170/175 and

EMBRAER 190/195 airplanes equipped respectively withCF34-8E and CF34-10E series engines, operating under ANAC,FAA, EASA/JAA and TCCA certifications.

SOPM1755-001

DECEMBER 10, 2003TEMP. REVISION 15.1 NOVEMBER 09, 2012

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Copyright 2012 by EMBRAER S.A.. All rights reserved. This document shall not be copied or reproduced, whether inwhole or in part, in any form or by any means without the express written authorization of Embraer. The information,technical data, designs and drawings disclosed in this document are property information of Embraer or third parties

and shall not be used or disclosed to any third party without permission of Embraer.

EMBRAER 170/175/190/195

STANDARD OPERATING PROCEDURESMANUAL

EMBRAER S.A.

This manual is applicable to EMBRAER 170/175 and

EMBRAER 190/195 airplanes equipped respectively withCF34-8E and CF34-10E series engines, operating under ANAC,FAA, EASA/JAA and TCCA certifications.

SOPM1755-001

DECEMBER 10, 2003REVISION 15 JULY 16, 2012

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CUSTOMER COMMENT FORM

STANDARD OPERATING PROCEDURES MANUAL

SOPM-1755

Please use this Customer Comment Form to notify us of

any discrepancies or problems found in the StandardOperating Procedures Manual. We also welcome

constructive 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 Operations Support

Please return this form to:

Embraer - Flight Operations Support - PC176Av. Brigadeiro Faria Lima, 2170

CEP 12227-901So Jos dos Campos - SP - BRASIL

P.O. Box 8050

Phone: +55 12 3927-1706Fax: +55 12 3927-2477E-mail: [email protected]

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Section/Page/Code: Revision of the Page:

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 taken:

Proposed date for implementation: Implemented:

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REVISION 15 Page 1

SOPM-1755c01

HIGHLIGHTS OF CHANGE

The changes in this document are recognized by a vertical bar on the

edge of the page matching with the changed lines. This bar will reflectthe document revision number located at the bottom right of eachpage.

Here are presented the summary of these changes.

REVISION 15 JUL 16, 2012

Block Page Change Description

2-13 2

Changed the procedure steps sequence to improvethe crew workflow during power up. The EICASmessages now should be checked before GPUbutton is pushed in.

2-13 4 Included the test procedure of Universal DVDR.

2-13 4Added information on the Cockpit Door ControlPanel Check procedure.

2-153 and

11

Added information to clarifie that the inspection ofthe Wing Tank Water Drain Valve is applicable onlyto E170/175 Airplanes.

2-154 and

10Added the information about the allowable size ofoil puddle on Engine tail pipe.

2-17 9Added descriptive information regarding the step topress the TOGA Button.

2-17 12 Editorial Correction.

2-17 12Included information regarding Engine Start withstrong tailwind.

2-31 1

Added information regarding Thrust Leversposition. During takeoff the thrust lever should beset to 40% N1 to check engine stabilization beforesetting the thrust levers to TOGA detent.

2-35 2 Editorial correction.

2-65 1Added recommended bleed duct pressure forengine start as a function of temperature andaltitude ASL according to FOL 170-2011-043.

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3-05-01 1 Editorial correction.

3-05-10 6 Editorial correction.

3-10 2 Added information about Engine Start with tailwind.

3-10 6 Added LOAD SHED EICAS message logic.


3-10 13

Improved procedure description to clarify that theElectric Hydraulic Pump 1 must be kept ON when

performing a single engine taxi with engine 1shutdown.

3-10 16Added information set Flap Lever to 5 after thecomplete stop of the airplane, before performing aemergency evacuation situation.

3-10 17Changed from Selects Flap 5 to Set Flap Lever to 5on the EMERGENCY EVACUATION Actions andCallouts Table.

3-15-01 7 Replaced "Flaps" by "Slats/Flaps".

3-15-05 9Added information about the setup of the FMSDEP/APP SPD page when using FMS SPEEDSwith NOISE ABATEMENT PROCEDURES.

3-15-05 10

Added the picture to show the Departure AreaVertical Limit, Departure Area Horizontal Limit andSpeed Limits when using FMS Speeds with NOISEABATEMENT TAKEOFF NADP1 / ICAO A.

3-15-05 12

Added the picture to show the Departure AreaVertical Limit, Departure Area Horizontal Limit andSpeed Limits when using FMS Speeds with NOISEABATEMENT TAKEOFF NADP2 / ICAO B.

3-15-10 9 to 12Changed wording from ON TAKEOFF AFTER V1toON TAKEOFF ABOVE V1, to harmonize with othersections of the manual.

3-20 4 Included callout when passing 10000 FT AFE in theCLIMB Action and Callouts table.

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3-25 6

Changed the procedure text to clarify that, the

guidance to detect fuel leak by comparing theEICAS fuel indication with FMS fuel quantity is onlyapplicable if the airplane is flying with both enginesoperative.

3-25 8Added the information that the Autopilot should bemaintained engaged during severe turbulence.

3-25 9Added a table with levels of turbulence and itsdefinitions.

3-25 12B

Changed the callout text to harmonize the PF

callout with PNF callout regarding THRUST LEVER1 (2) IDLE.

3-25 20Corrected the information about the ground speedused by the FMS to calculate Hold leg time anddistance.

3-25 21

Changed from Airspeed Unreliable to Unreliableairspeed to harmonize with others operationalmanuals. Updated the Unreliable Airspeed

background text.

3-25 25

Updated the Stall Recovery background text toclarify that, when in icing conditions, the stickshaker, PLI and LSA are adjusted to cope with theicing situation.

3-25 27Added the STALL callout to the Stall RecoveryACTIONS and CALLOUTS table.

3-35-01 7

Changed the text to clarify that, if the EICASmessage STAL PROT ICE SPEEDS becomes

active, the land speeds should be adjusted for ICEACCRETION for both normal and abnormalapproaches.

3-35-0110 and

11

Included guidance to deal with malfunctions duringapproaches. These guidelines are applicable to alltypes of approaches.

3-35-01 19Changed the text of the Action and Callotus table toclarify that the PF remains with the decision aboutadequacy for safe landings.

3-35-01 20Updated the text of note (3) to clarify that the PFremains with the decision about adequacy for safelandings.

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3-35-05 11

Changed the LOW VISIBILITY APPROACH

ACTIONS AND CALLOUTS table to inform that thecrew should select flap 3 and landing gear downwhen on one dot to intercept glide or on finalinbound before FAF.


3-35-05 16Added the information that the rudder trim must be

set to zero when stabilized on short final.

3-35-10 7Changed ACTIONS and CALLOUTS text toharmonize it with others approach procedures.

3-35-10 8Changed the text of the ACTION and CALLOUTStable to clarify that the CALLOUT LANDING shouldbe performed at least at minimums.


3-35-10 10Added the information that the rudder trim must beset to zero when stabilized on short final.

3-35-10 20

Changed the Normal Go Around procedures toselect VNAV when reaching 1000 ft AGL orobstacle clearance altitude. This modificationharmonizes this procedure with the normal Takeoff.

3-35-10 22Changed Action and Callouts table of the NormalGo around. This modification harmonizes this

procedure with the normal Takeoff.3-35-10 22

Added note (1) to clarify that crew should selectFMS only if it is not already the navigation source.

3-35-10 26Removed the ENGINE FAILURE DURING FINALAPPROACH guidelines. These guidelines are nowpresented in 3-35-01.

3-40 2Changed the wording of the runway touchdownzone definition.

3-40 6AAdded the OPERATIONAL FACTORSAFFECTING LANDING DISTANCE descriptive textand graphic.

3-40 6BAdded the OPERATIONAL FACTORSAFFECTING LANDING DISTANCE graphic.

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3-40 8

Added information about precautions that should

be taken when windshear is suspected duringlanding.


3-40 22

Updated the Action and Call Out table to changethe term "GEAR DOWN" to "LANDING GEARDOWN" in order to harmonize de terms through themanual.

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RECORD OF TEMPORARY REVISIONS

SOPM1755-001

TR 15.1 ............................................................................ NOV 09, 2012

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LIST OF EFFECTIVE PAGES

ORIGINAL................ 0....................DEC 10, 2003REVISION................ 1.................... FEB 20, 2004REVISION................ 2....................MAY 31, 2004REVISION................ 3....................DEC 23, 2004REVISION................ 4....................AUG 07, 2006REVISION................ 5....................MAY 29, 2007REVISION................ 6.....................JUL 31, 2007REVISION................ 7.................... JUN 30, 2008REVISION................ 8....................NOV 20, 2008

REVISION................ 9....................AUG 03, 2009REVISION................ 10..................DEC 18, 2009REVISION................ 11..................APR 30, 2010REVISION................ 12..................AUG 26, 2010REVISION................ 13..................MAY 30, 2011REVISION................ 14.................. SEP 19, 2011REVISION................ 15................... JUL 16, 2012

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0-TOC1 ...................REVISION 102 ...................REVISION 10

1-001 ...................REVISION 102 ...................REVISION 10



2-071 ...................REVISION 112 ...................REVISION 113 ...................REVISION 104 ...................REVISION 10

2-091 ...................REVISION 12

2 ...................REVISION 13

2-131 ...................REVISION 12

* 2 ...................REVISION 15

* 3...................REVISION 15* 4...................REVISION 15* 5...................REVISION 15

* 6...................REVISION 15

2-151...................REVISION 142...................REVISION 14

* 3...................REVISION 15* 4...................REVISION 15* 5...................REVISION 15

* 6...................REVISION 15* 7...................REVISION 15

8...................REVISION 149...................REVISION 14

* 10................. REVISION 15* 11................. REVISION 15* 12................. REVISION 15

2-171...................REVISION 102...................REVISION 103...................REVISION 124...................REVISION 135...................REVISION 136...................REVISION 127...................REVISION 138...................REVISION 12

* 9...................REVISION 15* 10................. REVISION 15

11................. REVISION 11* 12................. REVISION 15* 13................. REVISION 15* 14................. REVISION 15

2-25


2-291...................REVISION 12

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2-31

* 1...................REVISION 152...................REVISION 10


2-34


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* 2...................REVISION 15

2-37





2-491...................REVISION 14

2...................REVISION 10

2-531...................REVISION 10

2................... REVISION 10

2-60

1................... REVISION 122................... REVISION 12

2-631................... REVISION 122................... REVISION 12

2-65

* 1................... REVISION 15* 2................... REVISION 15


2-70

1................... REVISION 142................... REVISION 12


2-751................... REVISION 122................... REVISION 133................... REVISION 124................... REVISION 125................... REVISION 126................... REVISION 127................... REVISION 128................... REVISION 12

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1 ...................REVISION 132 ...................REVISION 12


3-00

1 ...................REVISION 102 ...................REVISION 103 ...................REVISION 124 ...................REVISION 105 ...................REVISION 136 ...................REVISION 117 ...................REVISION 118 ...................REVISION 10

3-05-01* 1 ...................REVISION 15

2 ...................REVISION 113 ...................REVISION 114 ...................REVISION 115 ...................REVISION 116 ...................REVISION 117 ...................REVISION 118 ...................REVISION 109 ...................REVISION 1010 .................REVISION 10

3-05-051 ...................REVISION 102 ...................REVISION 103 ...................REVISION 10

4 ...................REVISION 115 ...................REVISION 116 ...................REVISION 117 ...................REVISION 108 ...................REVISION 10

3-05-101...................REVISION 102...................REVISION 10

3...................REVISION 104...................REVISION 105...................REVISION 10

* 6...................REVISION 157...................REVISION 148...................REVISION 109...................REVISION 1010................. REVISION 10

11................. REVISION 1412................. REVISION 1013................. REVISION 1014................. REVISION 1315................. REVISION 1016................. REVISION 10

3-10

1...................REVISION 12* 2...................REVISION 153...................REVISION 134...................REVISION 115...................REVISION 13

* 6...................REVISION 15* 7...................REVISION 15

8...................REVISION 129...................REVISION 1210................. REVISION 1011................. REVISION 1012................. REVISION 12

* 13................. REVISION 1514................. REVISION 1415................. REVISION 14

* 16................. REVISION 15* 17................. REVISION 15

* 18................. REVISION 15

3-15-011...................REVISION 132...................REVISION 12

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6...................REVISION 11* 7...................REVISION 15

8...................REVISION 10

3-15-051...................REVISION 142...................REVISION 142A ................REVISION 13

2B ................REVISION 133...................REVISION 104...................REVISION 105...................REVISION 106...................REVISION 107...................REVISION 138...................REVISION 13

* 9...................REVISION 15

* 10................. REVISION 15* 11................. REVISION 15* 12................. REVISION 15* 13................. REVISION 15* 14................. REVISION 15* 15................. REVISION 15* 16................. REVISION 15* 17................. REVISION 15* 18................. REVISION 15

3-15-101...................REVISION 102...................REVISION 113...................REVISION 114...................REVISION 105...................REVISION 106...................REVISION 11


* 9...................REVISION 15* 10................. REVISION 15* 11................. REVISION 15

* 12................. REVISION 15

3-20

1................... REVISION 132................... REVISION 103................... REVISION 10

* 4................... REVISION 155................... REVISION 116................... REVISION 10

3-25

1................... REVISION 102................... REVISION 103................... REVISION 104................... REVISION 105................... REVISION 10

* 6................... REVISION 157................... REVISION 10

* 8................... REVISION 15

* 9................... REVISION 15* 10................. REVISION 15* 11................. REVISION 15* 12................. REVISION 15* 12A .............. REVISION 15* 12B .............. REVISION 15

13................. REVISION 1214................. REVISION 1215................. REVISION 1416................. REVISION 1017................. REVISION 1418................. REVISION 1119................. REVISION 11

* 20................. REVISION 15* 21................. REVISION 15

22................. REVISION 1023................. REVISION 10

24................. REVISION 14* 25................. REVISION 15

26................. REVISION 14* 27................. REVISION 15

28................. REVISION 14

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3 ...................REVISION 134 ...................REVISION 115 ...................REVISION 106 ...................REVISION 10

3-35-011 ...................REVISION 112 ...................REVISION 14

3 ...................REVISION 114 ...................REVISION 105 ...................REVISION 146 ...................REVISION 10

* 7 ...................REVISION 158 ...................REVISION 109 ...................REVISION 11

* 10 .................REVISION 15

* 11 .................REVISION 15* 12 .................REVISION 15* 13 .................REVISION 15* 14 .................REVISION 15* 15 .................REVISION 15* 16 .................REVISION 15* 17 .................REVISION 15* 18 .................REVISION 15* 19 .................REVISION 15* 20 .................REVISION 15

3-35-051 ...................REVISION 102 ...................REVISION 103 ...................REVISION 104 ...................REVISION 115 ...................REVISION 11

6 ...................REVISION 107 ...................REVISION 108 ...................REVISION 109 ...................REVISION 1010 .................REVISION 12

* 11................. REVISION 1512................. REVISION 1312A ..............REVISION 13

12B ..............REVISION 13* 13................. REVISION 15

14................. REVISION 1015................. REVISION 13


3-35-101...................REVISION 102...................REVISION 103...................REVISION 104...................REVISION 105...................REVISION 126...................REVISION 107...................REVISION 13

* 8...................REVISION 159...................REVISION 13* 10................. REVISION 15

11................. REVISION 1312................. REVISION 1313................. REVISION 1314................. REVISION 1314A ..............REVISION 1414B ..............REVISION 1415................. REVISION 1416................. REVISION 1017................. REVISION 1118................. REVISION 1019................. REVISION 11

* 20................. REVISION 1521................. REVISION 10

* 22................. REVISION 15

23................. REVISION 1024................. REVISION 1025................. REVISION 10

* 26................. REVISION 1527................. REVISION 11

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3-401...................REVISION 10

* 2...................REVISION 153...................REVISION 114...................REVISION 145...................REVISION 146...................REVISION 14

* 6A ................REVISION 15* 6B ................REVISION 15

7...................REVISION 11* 8...................REVISION 15* 8A ................REVISION 15* 8B ................REVISION 15

9...................REVISION 1110................. REVISION 11

11................. REVISION 1112................. REVISION 1113................. REVISION 1114................. REVISION 1115................. REVISION 1116................. REVISION 1117................. REVISION 1118................. REVISION 1419................. REVISION 1120................. REVISION 1121................. REVISION 11


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REVISION 10 Page 1SOPM-1755

TABLE OF CONTENTS

1 - INTRODUCTION

2 - NORMAL PROCEDURES

3 - PROCEDURES AND TECHNIQUES

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SECTION 1

INTRODUCTION

TABLE OF CONTENTS

Block Page

Introduction ........................................................................1-05.......... 01

Procedural Deviation and Its Relation to Safety...........1-05.......... 02

Airplane Sophistication and Checklists ........................1-05.......... 02

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INTRODUCTION

The SOP provides information and guidance for the efficient operationof the E-Jets.

This manual is not a replacement of any of the operational manualsrequired by applicable regulations such as the Airplane Flight Manualor the Company Operations Manual.

This SOP is optimized for passenger-carrying operation in acommercial airline environment and the philosophy behind this manualis based on reducing crew workload while maintaining the highest

possible level of safety.Standard operating procedures are a set of procedures that serve toprovide common ground for all crewmembers, usually unfamiliar witheach other's experience and technical capabilities. In a well-standardized operation, another qualified pilot could replace an activecockpit crewmember during the flight, and the operation wouldcontinue safely and smoothly.

The Normal Procedures section presents the AFM/AOM Normal

Procedures. The intention is to eliminate any doubts regarding FlightStandards that may occur during the operation of the airplane.

The Procedures and Techniqu es section brings operationalpractices and flight profiles to a standard cockpit concept throughoutflight phases. It has directives related to how the operation should beconducted. Topics like Crew Coordination, Captain authority and

Areas of responsibility are included.

It also contains guidelines to be observed should a specific situation

arise regardless of when and where it occurs during the flight. Topicssuch as handling of the autopilot and task sharing when hand-flyingthe airplane are covered in those sections.

Information regarding Low Visibility standardizes the procedures underthis scenario emphasizing the crew coordination and presents theconfigurations approved to perform the operation with low visibilitydivided in flight phases.

Emergency/Abnormal Procedures are also presented according to itsflight phase in the Procedures and Techniques section. It ispresented some AFM/AOM Emergency/Abnormal Procedures in adetailed manner. The intention is to guide the crew on how to performthe required tasks to correct a situation or condition. Only the QRHprocedures requiring high level of crew coordination are presented.

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1-05


PROCEDURAL DEVIATION AND ITS RELATION TO

SAFETY

The highest percentage of problems that generate crew-causedaccidents and incidents manifest themselves in the form of proceduraldeviation. If the flight goes well, these deviations are not perceivedand in most cases are left unresolved but they become apparentfollowing an incident or an accident.

AIRPLANE SOPHISTICATION AND CHECKLISTSThe degree of technological sophistication in the design of this familyof airplanes directly affects the checklist. On older airplanes, the flightcrew must manually select and monitor most items. In more advancedairplanes the same items are accomplished by automatic systems thatrelieve the flight crew of these tasks. Checklists for these airplanestend to be shorter and simpler but require a more careful task analysiswith improved monitoring skills.

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SECTION 2

NORMAL PROCEDURES

TABLE OF CONTENTS

Block Page

Normal Checklist................................................................2-07.......... 01

Internal Safety Inspection ..................................................2-09.......... 01

Power Up ...........................................................................2-13.......... 01

External Inspection ............................................................2-15.......... 01

Before Start........................................................................2-17.......... 01

Engine Start..................................................................2-17..........12

After Start...........................................................................2-25.......... 01

Before Takeoff ................................................................... 2-29.......... 01

Takeoff...............................................................................2-31.......... 01

After Takeoff ......................................................................2-33.......... 01

Climb..................................................................................2-34.......... 01

Descent..............................................................................2-35.......... 01

Approach ...........................................................................2-37.......... 01

Before Landing ..................................................................2-41.......... 01

Go Around .........................................................................2-42.......... 01

After Landing ..................................................................... 2-45.......... 01

Shutdown...........................................................................2-49.......... 01

Leaving the Airplane.......................................................... 2-53.......... 01

ECS OFF Takeoff ..............................................................2-60.......... 01

Engine Crossbleed Start....................................................2-63.......... 01

Engine Ground Pneumatic Start........................................2-65..........01

Engine Battery Start...........................................................2-67.......... 01

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Block Page

Single Engine Taxi .............................................................2-70 ..........01

Hot Weather.......................................................................2-73 ..........01

Ice Conditions, Cold Weather and Cold Soak ...................2-75 ..........01

Lightning Strike ..................................................................2-77 ..........01

Turbulent Air Penetration...................................................2-80 ..........01

Windshear..........................................................................2-83 ..........01

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REVISION 11 Page 1

SOPM-1755

NORMAL CHECKLIST

INTERNAL SAFETY INSPECTION

CHALLENGE ACTION PERFORMED BY

Maintenance Status...........CKD .........................LSP/RSPCockpit Emer Equip...........CKD ................................ RSPELECTRIC Panel...............SET ................................. RSPFUEL Panel .......................CKD ................................ RSPWindshield Wiper...............OFF................................. RSPHYDRAULIC Panel............CKD ................................ RSPAIR COND/PNEU Panel....CKD ................................ RSP

PAX OXY Panel.................CKD ................................ RSPELT ....................................ARM ................................ RSPLanding Gear Lever...........DOWN............................. RSPSTART/STOP Selectors....STOP .............................. RSPSpeed Brake Lever............CLOSED ......................... RSPRAT Manual Deploy ..........STOWED ........................ RSPSLAT/FLAP Lever..............VERIFY POS .................. RSPCircuit Breakers .................CKD ................................ RSP

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POWER UPCHALLENGE ACTION PERFORMED BY

CAUTION: ENSURE THE AIRPLANE IS NOT MOVEDBEFORE THE IESS IS INITIALIZED.

Battery 1 ............................ON................................... RSPBattery 2 ............................AUTO .............................. RSP

CAUTION: VERIFY THAT ONLY DISPLAYS 2 AND 3ARE AVAILABLE. IF MORE THANDISPLAYS 2 AND 3 ARE AVAILABLE, THE

AIRPLANE MUST NOT BE DISPATCHED.

Battery voltage...................CKD.................................RSPGPU Button (if applicable) .PUSHED IN..................... RSPFire Ext panel.....................CKD.................................RSPAPU....................................AS RQRD........................ RSPNAV light ............................ON................................... RSPHYDRAULIC panel ............AS RQRD........................RSP

Electronic CBs ...................CKD..................................LSPElectronic Checklist

(if applicable) ................CKD.................................RSPDVDR panel .......................CKD.................................RSPCockpit reinforced door

panel (if applicable) ......CKD................................. RSPPhotoluminescent Strips ....CKD.................................RSP

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REVISION 10 Page 3

SOPM-1755

BEFORE STARTCHALLENGE RESPONSE ANSWERED BY

Pax signs panel .................SET..................................LSP

PRESSURIZATION Panel.SET..................................LSPOxygen masks...................CKD .........................LSP/RSPFlight instruments ..............X-CKD..............................LSPThrust levers......................IDLE .................................LSP------------------------------------------------------------------------------------------------Fuel QTY ...........................CKD .........................LSP/RSPMCDU................................SET ..................................LSPTRIM Panel........................___ SET/ZERO/ZERO.....LSP

Doors & windows...............CLSD .......................LSP/RSPRed beacon .......................ON....................................LSPEmergency/Parking brake.AS RQRD.........................LSP

AFTER STARTCHALLENGE RESPONSE ANSWERED BY

Ground equipment.............REMOVED.......................LSP

SLAT/FLAP........................___ SET...........................LSPFlight controls ....................CKD .................................LSP

BEFORE TAKEOFFCHALLENGE RESPONSE ANSWERED BY

Brakes temp ......................CKD ............................... ..LSPEICAS................................CKD .................................LSP

Transponder ......................TA/RA ..............................LSPTakeoff configuration.........CKD ............................... ..LSP

AFTER TAKEOFFCHALLENGE RESPONSE ANSWERED BY

Landing gear......................UP ....................................PNFSLAT/FLAP........................0 .......................................PNF

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APPROACHCHALLENGE RESPONSE ANSWERED BY

Pax signs panel .................SET ................................. PNFAltimeters...........................SET/X-CKD ................PF/PNF

BEFORE LANDINGCHALLENGE RESPONSE ANSWERED BY

Landing gear......................DOWN .......................PF/PNFSLAT/FLAP........................___ SET .....................PF/PNF

SHUTDOWNCHALLENGE RESPONSE ANSWERED BY

Emergency/Parking brake .SET .................................LSPSTART/STOP selectors.....STOP ...............................LSPHyd pump 3A .....................OFF ..................................LSP

LEAVING THE AIRPLANECHALLENGE RESPONSE ANSWERED BY

Pax signs panel .................OFF ..................................LSPGPU/APU...........................OFF ..................................LSPBatteries 1 and 2................OFF ..................................LSP

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2-09

REVISION 12 Page 1

SOPM-1755

INTERNAL SAFETY INSPECTION

The Internal Safety Inspection procedures must be performed beforethe Power Up on a particular airplane.


Maintenance Status..................................... CHECK.....LSP&RSP

Cockpit Emergency Equipment .................CHECK...............RSP

Check for the availability, status and proper location of thefollowing equipment:

Protective Breathing Equipment (PBE).

Fire Extinguishers.

Crash Axe.

Life Vests.

Escape Ropes.

Flashlights.

ELECTRIC Panel................................................SET ...............RSP

IDG 1 Selector.................................................... AUTOIDG 2 Selector.................................................... AUTO

AC BUS TIES Selector....................................... AUTOGPU Button ........................................................ PUSHED OUT

APU GEN Button................................................ PUSHED INTRU 1 ................................................................. AUTO

TRU ESS............................................................ AUTOTRU 2 ................................................................. AUTODC BUS TIES..................................................... AUTOBattery 1 Selector............................................... OFFBattery 2 Selector............................................... OFF

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FUEL Panel...................................................CHECK .............. RSP

Verify all fuel pump knobs in AUTO position and XFEED in thedesired position.

WINDSHIELD WIPER Selectors....................... OFF .............. RSP

HYDRAULIC Panel .......................................CHECK .............. RSP

SYS 1 ENG PUMP SHUTOFF Button................PUSHED OUTPTU Selector ......................................................AUTOSYS 2 ENG PUMP SHUTOFF Button................PUSHED OUTSYS 1 and 2 ELEC PUMP Selectors..................AUTOSYS 3 ELEC PUMP A ........................................ OFFSYS 3 ELEC PUMP B ........................................ AUTO

AIR COND/PNEUMATIC Panel ....................CHECK .............. RSP

Verify all buttons pushed in.

PASSENGER OXYGEN Panel .................... CHECK .............. RSP

Verify Masks Deploy Selector Knob in AUTO.

ELT .................................................................... ARM .............. RSP

Landing Gear Lever ...................................... DOWN .............. RSP

START/STOP Selectors..................................STOP .............. RSP

Speed Brake Lever ....................................CLOSED .............. RSP

RAT Manual Deploy ..................................STOWED .............. RSP

SLAT/FLAP Lever...................... VERIFY POSITION .............. RSPVerify and make sure that the actual SLAT/FLAP lever positionagrees with the surface position.

Circuit Breakers ...........................................CHECK .............. RSP

Verify both sidewall panels to ensure agreement withmaintenance status.

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REVISION 12 Page 1

SOPM-1755

POWER UP

The POWER UP procedures and checklist must be performed every

crews first flight of the day on a particular airplane or when a powerdown was required.

If receiving the airplane already powered up, verify compliance with allitems and perform FIRE EXTINGUISH panel, Electronic CBs andDVDR CONTROL panel.

CAUTION: ENSURE THE AIRPLANE IS NOT MOVED BEFORE THEIESS IS INITIALIZED.


Battery 1 .............................................................. ON ...............RSP

Battery 2 ..........................................................AUTO...............RSP

CAUTION: VERIFY THAT ONLY DISPLAYS 2 AND 3 AREAVAILABLE. IF MORE THAN DISPLAYS 2 AND 3 ARE

AVAILABLE, THE AIRPLANE MUST NOT BEDISPATCHED.

Batteries Voltage .........................................CHECK...............RSP

Verify batteries voltage at or above 22 V (ANAC/TCCAcertification) or 22.5 V (FAA/EASA certification).

If batteries voltage is between 21 V and 22 V (ANAC/TCCA

certification) or 21 V and 22.5 V (FAA/EASA certification),recharge the batteries prior to takeoff, through any AC source(including engines during taxi) for:

30 minutes if batteries temperature is at or above 0oC or;

35 minutes if batteries temperature is at or above -5oC and

below 0oC or;

40 minutes if batteries temperature is at or above -10oC and

below -5oC or;

50 minutes if batteries temperature is below -10oC;

If batteries voltage is below 21 V, report to maintenance.

NOTE: Minimize the time the airplane is left with batteries as theunique power source, to avoid discharging.

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EICAS Messages....................CHECK DISPLAYED .............. RSP

GPU Button (if applicable) ...................PUSHED IN .............. RSP

Verify AVAIL light illuminated before pushing in. When GPU is notavailable, or is not necessary, maintain GPU Button pushed out.

NOTE: - The Electrical PBIT is automatically performed after theairplane is powered by any AC source and takes about3 minutes to complete. The Electrical PBIT will be

interrupted if any electric hydraulic pump is running, theFLIGHT CONTROLS MODE Panel switches are cycled or ifAC power is interrupted while the test is running.

- A FLT CTRL TEST IN PROG Status message is displayed toinform the pilot that the Electrical PBIT is in progress.

- If the displays 2 and/or 4 are configured as PFD, set therespective reversionary panel selector knob to MFD then to

AUTO. After 8 seconds, the affected display configurationwill return to MFD.

FIRE EXTINGUISHER Panel (Overhead)....CHECK .............. RSP

Verify there are no fire protection fail messages displayed onthe EICAS after Power Up.

Press and hold the TEST button and observe the followingEICAS messages, lights and warnings:

Aural warning. Fire handles illuminated.

CARGO SMOKE FWD/AFT buttons illuminated.

APU button illuminated.

Upper half of the APU Emergency Stop Buttonilluminated.

WARNING lights flashing.

CARGO FWD (AFT) SMOKE EICAS message.

APU FIRE EICAS message. ENG 1 (2) FIRE EICAS message.

FIRE warning annunciation displayed inside ITTindicators.

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REVISION 15 Page 3

SOPM-1755


APU CONTROL Panel......................AS REQUIRED...............RSP

Verify EMER STOP Button is pushed out and not illuminated.

NOTE: If AC source is lost due to unintentional GPU or APU generatordisconnection, power down the airplane and perform the powerup procedure.

Navigation Light ................................................. ON ...............RSP

HYDRAULIC Panel...........................AS REQUIRED...............RSP

Only after the electrical PBIT is completed and if theFLT CTRL BIT EXPIRED EICAS message is displayed, performthe hydraulic panel checks.

Do not move any flight control surface. SYS 1 and 2 ELEC Pumps ON. SYS 3 ELEC PUMP A ON. Wait 1 minute. At this point the

FLT CTRL BIT EXPIRED EICAS message should extinguish.

SYS 1 and 2 ELEC Pumps AUTO. SYS 3 ELEC PUMP A OFF.

NOTE: - The FLT CTRL TEST IN PROGRESS Status message isdisplayed while hydraulic PBIT is in progress.

- If the FLT CTRL BIT EXPIRED EICAS message is stilldisplayed, power down the airplane and perform the powerup procedure.

Electronic CBs .............................................CHECK...............LSP

Select CB OUT/LOCK page on MCDU and check the CBsstatus to ensure agreement with maintenance status.

If the NEW TRIP prompt is displayed on the MCDU press it tocheck the electronic CBs status.

Electronic Checklist (if applicable)............ CHECK...............RSP

Verify that this ECL database corresponds to the paper QRHrevision present in the cockpit.

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DVDR CONTROL Panel ...............................CHECK .............. RSP

Honeywell DVDR: Press TEST Button and verify no failmessages displayed on EICAS.

Universal DVDR: Press and hold TEST for two seconds. Verifyno fail messages displayed on EICAS and observe thefollowing test result:

The FDR 1 and CVR 1 PASS/FAIL lights flash duringten seconds. After ten seconds the FDR 1 and CVR 1

PASS/FAIL lights illuminate steady in green, indicatingthe completion of a successful test.

After the DVDR 1 test finishes, the DVDR 2 test willautomatically start. Verify the following test result:

The FDR 2 and CVR 2 PASS/FAIL lights flash duringten seconds. After ten seconds the FDR 2 and CVR 2PASS/FAIL lights illuminate steady in green, indicatingthe completion of a successful test.

If a failure is found, the corresponding FDR/CVR fail lightindicator will illuminate steady in amber.

Electronic Flight Bag (if applicable).................. ON ...LSP & RSP

Cockpit ReinforcedDoor Panel (if applicable) ......................CHECK .............. RSP

Close the cockpit door; Press and hold the TEST button; Check DING-DONG alarm and UNLOCKED indication ON; Push in the LOCK button and check the electromechanical

latch normal operation; Press the EMERG ENTRY button on the door control panel in

the passenger cabin. Check the UNLOCKED indicationflashing and check normal operation of the DING-DONG alarm

sequence according to the system logic (refer to AOM 14-01-22 and 14-01-60);

Push out the LOCK button.

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REVISION 15 Page 5

SOPM-1755

Photoluminescent Strips ............................CHECK...............RSP

Check in the AOM section 3-05 how much time of ceiling andentrance lighting exposure in bright or daylight would be

necessary to charge the photoluminescent strips.

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INTENTIONALLY BLANK

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REVISION 14 Page 1SOPM-1755c01

EXTERNAL INSPECTIONThe External Inspection procedures are usually performed by the RSPprior to each flight.

While conducting the external inspection, pilots must be aware ofmoving vehicles around the airplane and surroundings.

In case of suspicious object is identified, inform immediately thesecurity staff.

Prior to starting the external inspection:

CHALLENGE ACTION

External Lights .......................................................AS REQUIREDIf the external lights check was not performed by themaintenance, turn the external lights ON and check them. Turnthe lights OFF immediately after check.

Emergency/Parking Brake ....................................ON

Check if there is sufficient hydraulic pressure to activate theEmergency/Parking Brake to check the Brake Wear Indicators.

Recommended walk-around sequence:

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1. LEFT FWD FUSELAGE

FWD Passenger Door ............................................CHECK

External Power Receptacle ...................................SECURED

Left Smart Probes/TAT Sensor/Ice Detector .......CHECK

Verify condition with no obstructions, covers or damage.

2. NOSE SECTION

Windshield Wipers .................................................CHECK

Radome ...................................................................CONDITION ANDLATCHED

Forward Avionics Compartment...........................SECURED

If not in use, visibly secured.

Lower FWD Antenna ..............................................CONDITION

Undamaged.

3. NOSE LANDING GEAR

Wheels and Tires ....................................................CONDITION

Up Lock Hook .........................................................UNLOCKED

Strut/Wheel Well/Doors .........................................CONDITION ANDNO LEAKS

Ground Locking Pin ...............................................REMOVED

Landing and Taxi Lights ........................................CONDITION

Clean and undamaged.

4. RIGHT FWD FUSELAGE

Right Smart Probes/TAT Sensor/Ice Detector.....CHECK

Verify condition with no obstructions, covers or damage.

(Continued)

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REVISION 15 Page 3

SOPM-1755c01

RAT Safety Lock Pin.............................................. REMOVED

FWD Service Door ................................................. CHECK


Oxygen Discharge Indicator................................. GREEN DISC

FWD Cargo Door.................................................... CHECK


5. LOWER CENTER FUSELAGE

Lower FWD Antennas/Fwd Drain Mast................ CONDITION

Undamaged.

Lower Red Beacon Light ...................................... CONDITION

Clean and undamaged

6. RIGHT CENTER WING

Wing Inspection Landing and Taxi Lights .......... CONDITION


Right Ram Air Inlet ................................................ NOOBSTRUCTION

No obstruction or damage.

Air Inlets and Outlets............................................. NOOBSTRUCTION


Collector Tank Water Drain Valve Door............... SECURED


Wing Tank Water Drain Valve............................... CONDITION ANDNO LEAKSApplicable only to E170/175 airplanes.


(Continued)

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Magnetic Level Indicators.....................................PUSHED IN ANDNO LEAKS

E170/175: Verify RH1 Magnetic Level Indicator.

E190/195: Verify RH1 and RH2 Magnetic Level Indicators.

Pylon .......................................................................CONDITION

7. ENGINE 2 LH SIDE

Engine Inlet.............................................................CONDITION

Check for FOs and leaks inside air inlet. Ensure that there is no

damage to the T12 Sensor and that the FADEC Cooling Inlet isclear

Fan Blades..............................................................CHECK

Check for damaged Fan Blades and ensure Fan is free to rotate.

Check for damages on spinner.

LH Nacelle Strake...................................................CONDITION

Anti-ice Pressure Relief Door ...............................CLOSED ANDLATCHED

LH Fan Cowl Doors................................................CONDITION ANDLATCHED

LH Thrust Reverser................................................CONDITION ANDLATCHED

Core Pressure Relief Door ....................................CLOSED

Turbine Exhaust.....................................................CLEAR AND NOLEAKS

After engine shutdown the scavenge system is no longer effective.A small amount of oil may leak through the aft sump drain and poolin the engine chevron nozzle.

E170/175: If the puddle size exceeds 4 in (102 mm), maintenance

should be contacted.

E190/195: If the puddle size exceeds 9 in x 6 in (229 mm x 152mm), maintenance should be contacted. For airplanes equippedwith Improved Acoustic Chevron Nozzle (IACN) the puddle shouldnot exceed 7.5 in x 4.5 in (190 mm x 114 mm). (Continued)

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REVISION 15 Page 5

SOPM-1755c01

8. ENGINE 2 RH SIDE

Core Pressure Relief Door....................................CLOSED

RH Thrust Reverser ............................................... CONDITION ANDLATCHED

RH Fan Cowl Doors ............................................... CONDITION ANDLATCHED

FADEC Cooling Vent ............................................. CLEAR

RH Nacelle Strake.................................................. CONDITION

Oil Fill Access Door............................................... CLOSED

9. RIGHT WING LEADING EDGE

Wing Leading Edges ............................................. CONDITION

Refueling Compartment Door .............................. SECURED

Magnetic Level Indicators..................................... PUSHED IN ANDNO LEAKS

E170/175: Verify RH2 and RH3 Magnetic Level Indicators.

E190/195: Verify RH3 Magnetic Level Indicator.

Access Doors and Panels..................................... SECURED

Pressure Relief Valve ............................................ CHECK

Wing Vents ............................................................. NOOBSTRUCTION

Navigation and Strobe Lights............................... CONDITION


10. RIGHT WING TRAILING EDGE

Static Dischargers ................................................. NUMBER ANDCONDITION

Verify 3 Static Discharges on the aileron and 6 on the winglet.Refer to the CDL for dispatch with missing items.

(Continued)

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Flight Control Surfaces and Fairings...................CONDITION

Surfaces clear and unobstructed.

11. RIGHT LANDING GEAR

Right Main Gear .....................................................CHECK

Wheels and Tires ...................................................CONDITION

Up Lock Hook.........................................................UNLOCKED

Strut/Wheel Wells...................................................CONDITION ANDNO LEAKS

Ground Locking Pin...............................................REMOVED

Brakes Wear Indicators .........................................CHECK

12. RIGHT AFT FUSELAGE

Access Doors and Panels.....................................SECURED


Drain Mast...............................................................CONDITION


AFT Cargo Door .....................................................CHECK


AFT Service Door...................................................CHECK


Lower AFT Antennas/AFT Drain Mast .................CONDITION

Undamaged.

Battery Air Outlet ...................................................NO

OBSTRUCTIONNo obstruction or damage.

(Continued)

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REVISION 15 Page 7

SOPM-1755c01

13. TAIL SECTION

Flight Control Surfaces......................................... CONDITION

Surfaces Clear and Unobstructed.

Empennages Leading Edges................................ CONDITION

Static Dischargers ................................................. NUMBER ANDCONDITION

E170/175: Verify 4 Static Dischargers on the rudder, 4 on eachelevator and 1 on vertical stabilizer.

E190/195: Verify 4 Static Dischargers on the rudder, 3 on eachelevator, 3 on each horizontal stabilizer and 1 on vertical stabilizer.

Refer to the CDL for dispatch with missing items.

APU ......................................................................... CONDITION

14. LEFT AFT FUSELAGE

APU External Power Receptacle.......................... CHECK


Overboard Vent...................................................... NOOBSTRUCTION


Pressurization Static Port..................................... NOOBSTRUCTION


Potable Water Service Panel ................................ SECURED


AFT PAX Door........................................................ CHECK


Lower AFT Antennas............................................. CONDITION

Undamaged.

(Continued)

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Access Doors and Panels.....................................SECURED


15. LEFT LANDING GEAR

Left Main Gear ........................................................CHECK

Wheels and Tires ...................................................CONDITION

Up Lock Hook.........................................................UNLOCKED

Strut/Wheel Wells...................................................CONDITION AND

NO LEAKS

Ground Locking Pin...............................................REMOVED

Brakes Wear Indicators .........................................CHECK

16. LEFT WING TRAILING EDGE

Flight Control Surfaces and Fairings...................CONDITION

Surfaces clear and unobstructed.

Static Dischargers .................................................NUMBER ANDCONDITION

Verify 3 static dischargers on the aileron and 6 static dischargerson the winglet. Refer to the CDL for dispatch with missing items.

Navigation, Strobe Lights

and Upper red Beacon Lights..........................CONDITIONClean and undamaged.

Upper Antennas .....................................................CONDITION

Undamaged.

17. LEFT WING LEADING EDGE

Wing Leading Edges..............................................CONDITION

(Continued)

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REVISION 14 Page 9

SOPM-1755c01

Wing Vents ............................................................. NOOBSTRUCTION

Pressure Relief Valve ............................................ CHECK

Access Doors and Panels..................................... SECURED

Wing Leading Edges ............................................. CONDITION

Magnetic Level Indicator....................................... PUSHED IN ANDNO LEAKS

E170/175: Verify LH3 and LH2 Magnetic Level Indicators.E190/195: Verify LH3 Magnetic Level Indicator.

18. ENGINE 1 LH SIDE

Engine Inlet ............................................................ CONDITION

Check for FOs and leaks inside air inlet. Ensure that there is nodamage to the T12 Sensor and that the FADEC Cooling Inlet is

clear

Fan Blades.............................................................. CHECK

Check for damaged Fan Blades and ensure Fan is free to rotate.

Check for damages on spinner.

LH Nacelle Strake .................................................. CONDITION

Anti-ice Pressure Relief Door............................... CLOSED ANDLATCHED

LH Fan Cowl Doors................................................ CONDITION ANDLATCHED

LH Thrust Reverser ............................................... CONDITION ANDLATCHED

Core Pressure Relief Door....................................CLOSED

Turbine Exhaust..................................................... CLEAR/NOLEAKS

(Continued)

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After engine shutdown the scavenge system is no longer effective.A small amount of oil may leak through the aft sump drain and poolin the engine chevron nozzle.

E170/175: If the puddle size exceeds 4 in (102 mm), maintenanceshould be contacted.

E190/195: If the puddle size exceeds 9 in x 6 in (229 mm x 152mm), maintenance should be contacted. For airplanes equippedwith Improved Acoustic Chevron Nozzle (IACN) the puddle shouldnot exceed 7.5 in x 4.5 in (190 mm x 114 mm).

19. ENGINE 1 RH SIDE

Core Pressure Relief Door ....................................CLOSED

RH Thrust Reverser ...............................................CONDITION ANDLATCHED

RH Fan Cowl Doors ...............................................CONDITION ANDLATCHED

FADEC Cooling Vent .............................................CLEAR

RH Nacelle Strake ..................................................CONDITION

Oil Fill Access Door ...............................................CLOSED

20. LEFT CENTER WING

Magnetic Level Indicators.....................................PUSHED IN ANDNO LEAKS

E170/175: Verify LH1 Magnetic Level Indicator.E190/195: Verify LH2 and LH1 Magnetic Level Indicators.

Landing, Taxi and Wing Inspection Lights..........CONDITION


Left Ram Air Inlet ...................................................NOOBSTRUCTION


(Continued)

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REVISION 15 Page 11

SOPM-1755c01

Air Inlets and Outlets............................................. NOOBSTRUCTION

Wing Tank Water Drain Valve............................... CONDITION ANDNO LEAKS

Applicable only to E170/175 airplanes.


Collector Tank Water Drain Valve Door............... SECURED


Air Conditioning Connection Access Door......... CHECK


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INTENTIONALLY BLANK

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REVISION 10 Page 1

SOPM-1755c01

BEFORE START

CHALLENGE ACTION / RESPONSE PERFORMED BY

Airplane Manuals & Documents..........ON BOARD...............RSP

Check all the required documents including:

Technical log.

AOM.

QRH.

If applicable, verify if the ECL database version iscompatible with the paper QRH revision.

Airworthiness certificate.

Weight and balance.

Radio station certificate.

Nav kit.

Jump Seat Oxy Mask, Regulatorsand Audio Panel .....................................CHECK ...............RSP

The RSP must verify the observers masks. Carry out the test as follows:

Set the regulator control knob to 100%.

Press and hold the TEST/RESET Button.

Verify a short illumination or blink of the flow indicator.

Verify audible oxygen flow in the headset orloudspeakers.

Once the mask fully pressurizes the indicator must goout, showing that the system is leak free.

Release the TEST/RESET Button.

ELECTRIC Panel ................................................SET ...............RSP

IDG 1 Selector .................................................... AUTOIDG 2 Selector .................................................... AUTOAC BUS TIES Selector....................................... AUTOGPU Button ........................................................ AS REQUIREDAPU GEN Button................................................ PUSHED IN

TRU 1 ................................................................. AUTOTRU ESS............................................................ AUTOTRU 2 ................................................................. AUTODC BUS TIES..................................................... AUTOBattery 1 Selector ............................................... ONBattery 2 Selector ............................................... AUTO

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COCKPIT LIGHTS Panel ................. AS REQUIRED .............. RSP

Adjust MAIN PNL, OVHD PNL and PEDESTAL lights.

Push ANNUCIATORS TEST button and verify all associated

lights.

Set DOME light as required.

Engine 1 Fire Handle ................................STOWED .............. RSP

FUEL Panel .........................................................SET .............. RSP

FUEL XFEED selector as required.

DC PUMP selector AUTO.

AC PUMP 1 and AC PUMP 2 selectors AUTO.

For ETOPS operation perform the Ejector Fuel Pump Check Valveaccording to the AOM SUPPLEMENTARY PROCEDURES ETOPS.

PASSENGER SIGNS Panel ...............................SET .............. RSP(Answered by LSP)

Emergency lights selector knob ON and verify EMERG LT

ON and EMERG LT NOT ARMED appear on the EICAS.

Emergency lights selector knob ARMED.

STERILE light as required.

Turn NO SMKG ON (NO ELEC DEVICES in someconfigurations).

Turn FSTN BELTS ON after finishing refueling the airplane.

FIRE EXTINGUISHER Panel ........................CHECK .............. RSP CARGO SMOKE FWD/AFT Buttons PUSHED OUT and no

lights.

APU fire extinguishing Button PUSHED OUT and no lights.

APU CONTROL Panel..................... AS REQUIRED .............. RSP

Emergency stop button pushed out and not illuminated.

EXTERNAL LIGHTS Panel.............. AS REQUIRED .............. RSP

Engine 2 Fire Handle ................................STOWED .............. RSP

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HYDRAULIC Panel...............................CHECK/SET ...............RSP

Verify ENG PUMP SHUTOFF 1 and 2 Buttons with no lightsand guarded.

Verify PTU Selector to AUTO.

Verify the HYDRAULIC SYS 1 and SYS 2 ELEC PUMPs toAUTO.

Verify the HYDRAULIC SYS 3 ELEC PUMP A to OFF.

Verify the HYDRAULIC SYS 3 ELEC PUMP B to AUTO.

PRESSURIZATION Panel ..................................SET ...............RSP(Answered by LSP)

CABIN ALT Selector knob STOP.

MODE Selector knob AUTO.

DUMP Button, no lights and guarded.

LFE Selector knob STOP.

WINDSHIELD HEATING button ........... PUSHED IN ...............RSP

ICE PROTECTION Panel ...................................SET ...............RSP

WINDSHIELD, ENGINE 1 and ENGINE 2 ButtonPUSHED IN;

Mode Selector Knob AUTO;

WING Button PUSHED IN;

TEST Selector knob OFF.

AIR COND/PNEUMATIC Panel..........................SET ...............RSP

COCKPIT and PAX CABIN temperature control as required.

RECIRC, PACK 1, PACK 2, XBLEED, BLEED 1,APU BLEED and BLEED 2 buttons pushed in.

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PASSENGER OXYGEN Panel ...........................SET .............. RSP

Mask Deploy selector knob AUTO.

MASK DEPLOYED indicator no light.

HGS Combiner (If Applicable) ..........................SET ...LSP & RSP

The LSP (and the RSP dual installation) must move thecombiner to the operating position detent, remove the cover,verify that the ALIGN HUD message is not displayed andadjust the brightness.

Oxygen Masks & Regulators ........... CHECK/100% ...LSP & RSP(Answered by LSP/RSP)

Check masks for supply of oxygen and for microphonefunctionality.

The MFD STATUS page must be checked and the availableoxygen supply and pressure must be adequate for use.

Carry out the test as follows:

Set the regulator control knob to 100%.

Press and hold the TEST/RESET Button.

Verify a short illumination or blink of the flow indicator. Verify audible oxygen flow in the headset or

loudspeakers.

Once the mask fully pressurizes the indicator must goout, showing that the system is leak free.

Release the TEST/RESET Button.

Glareshield Lights Control Panel .. AS REQUIRED ...LSP & RSP

DISPLAY CONTROLLER Panel.........................SET ...LSP & RSP

Set BARO SET knob to actual pressure.

Push HSI button for Full Compass, ARC or MAP.

Select the FMS as the primary NAV source (if raw datainformation is intended, use preview mode or Bearingpointers).

For HGS LVTO operations, set V/L.

BRG circle () to OFF, VOR1, ADF1 or FMS1 as required. BRG diamond () to OFF, VOR2, ADF2 or FMS2 as

required.REVERSIONARY PANEL...................................SET ...LSP & RSP

Displays selector knob in AUTO.

Sensors selectors (ADS/IRS) pushed out.

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Flight Instruments ..................................SET/XCKD...LSP & RSP

(Answered by LSP)

Verify:

Airspeed tapes not showing speed.

Set altimeter setting and cross check it with the fieldelevation.

EADIs leveled and flag-free.

Initial assigned altitude on the ALT SEL.

Altitude tape indications cross-check.

Both VSIs showing zero.

EHSIs with the courses selected according to theintended departure procedure and NAV source selected.

For LVTO using the HGS set the CDI to the runwaycourse.

EHSIs and magnetic compass flag free and showing thesame magnetic heading.

Heading bug set according to the proposed departureprocedure.

Check IESS and adjust the altimeter setting. Weather set on PFD and/or MFDs MAP page as required.

It is recommended that PNF sets the Terrain on MFD upto MSA.

Set the MFDs MAP page menu as required.

TCAS should be always displayed on both MFDs.

STATUS Page...............................................CHECK ...LSP & RSP

Verify on the status page ENG OIL LEVEL and BRAKESEMER ACCU pressure.

LSP should select FLIGHT CONTROL synoptic page.

RSP should remain on STATUS synoptic page.

AUTOBRAKE (If Applicable)............................ RTO ...............LSP

GND PROX TERR INHIB Button.................CHECK...............LSP

Verify button pushed out and no striped white bar illuminated.

EICAS............................................................CHECK...............LSP

Check EICAS messages to ensure agreement with airplane status.

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Clock ...................................................................SET .............. RSP

Select GPS on the GPS/INT/SET Selector. If the clock displays

dashes (-- -- --), adjust the clock INT position.

GND PROX G/S INHIB Button.....................CHECK .............. RSP

Verify no striped white bar illuminated.

LG WRN INHIB Button.................................CHECK .............. RSP

Verify no striped white bar illuminated.

FLIGHT CONTROLS MODE Panel ..............CHECK ...............LSP

Verify ELEVATORS, RUDDER and SPOILER Buttons guardedand no striped white bar illuminated.

SHAKER 1 and 2 CUTOUT Buttons............CHECK ...............LSP

Verify the SHAKER 1 CUTOUT and SHAKER 2 CUTOUTbuttons pushed out and no striped white bars illuminated.

IGNITION Selector Knobs ............................. AUTO ...............LSP

EICAS FULL..................................................CHECK ...............LSP

Verify the EICAS Full button in the desired position.

Speed Brake Lever ....................................CLOSED ...............LSP

Thrust Levers ................................................... IDLE ...............LSP

(Answered by LSP)

GND PROX FLAP OVRD..............................CHECK .............. RSP

Verify button pushed out, guarded and no striped white barilluminated.

AUDIO CONTROL Panel................. AS REQUIRED ...LSP & RSP

Select the microphone and audio reception buttons as requiredand adjust the volume levels. To avoid background noise do notset the SPKR volume higher than 55.

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TRIM Panel ...................................................CHECK...LSP & RSP

Verify that ROLL, YAW and PITCH (Captain, First Officer and

Backup) trims are operating properly both ways and check thatPosition Indication on EICAS changes accordingly. Verifysystems 3 second protection working properly. Adjust YAW andROLL trims to the neutral position and PITCH trim to the greenband.

NOTE: The PITCH TRIM Backup Switch may be checked once aday only, by flight crew or maintenance personnel, at theoperators discretion.

Pre-Mod. LOAD 21.2

NOTE: The SPOILER FAULT EICAS message may bedisplayed during the ROLL trim check and removedwhen all hydraulic systems are pressurized.

Flight Control DISCONNECT Handles.......CHECK...............RSP

Alternate GearExtension Compartment........................CHECK...............RSP

Verify the alternate gear extension lever is fully down and theelectrical override switch is in the NORMAL position.

MCDU..................................................................SET ...LSP & RSP

(Answered by LSP)

On PROGRESS page, activate the FMS AUTOTUNE bydeleting the NAV1 frequency for FMS1 and NAV2 frequencyfor FMS2 displayed on LSK 5L and 5R, respectively. In caseof FMS AUTOTUNE OFF takeoff is selected in order tohard-tune a specific VOR, return to FMS AUTOTUNE ON assoon as the VOR frequency is no longer necessary.

It is recommended that PF sets the route in the FMSaccording to the flight plan and both pilots check course,

distance, time, altitude on each waypoint and LFE in theEICAS according to the destination landing field elevation;

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It is recommended that PF sets on PERF INIT page 1/1 theCLIMB, CRUISE, DESCENT and DEP/APPROACH speedschedule, select page 2/3 and check/set its contents, onpage 3/3 set all fields with the available data;

If applicable select MENU HGS page and set theCOMBINER MODE;

If applicable (ETOPS configuration), select ETOPS or nonETOPS flight on MENU MISC MENU OPR CONFIGPage;

If applicable (AUTOLAND configuration), select enable ordisable on MENUMISC MENUOPR CONFIG Page.

Pre-Mod. LOAD 21.2

Select FLIGHT SUMMARY page and reset fuel used.

--------------------------SHORTLY BEFORE STARTUP-------------------------


FUEL QTY .....................................................CHECK ...LSP & RSP

(Answered by LSP & RSP)

MCDU ..................................................................SET ...LSP & RSP(Answered by LSP)

Insert the intended SID or the departing runway on the FMSand both pilots must check the accuracy of the procedureretrieved by FMS database. Select LNAV if intended totakeoff with lateral mode armed on ground.

For HGS operation if the previous action is not possibleselect MENU HGS page and check the Runway Length and

Elevation. Set the Performance initialization data on PERF INIT page. If

it is already available enter the zero fuel weight and pressCONFIRM INIT prompt on page 3/3. If performance isconfirmed and taking off with vertical mode armed on groundis desired, select VNAV.

Select T/O DATASET MENU page on the MCDU and set thedata below:

Thrust rate mode (TO-1, TO-2 or TO-3).

TO TEMP (__C).

ATTCS ON or OFF.

REF ECS (ON or OFF).

REF A/I (OFF, ENG or ALL).

FLEX T/O (ON or OFF).

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R

1

13O 2

12O

14O FS

4O

1OO

EM170AOM980001.D

GN

FLEX TEMP (__C).

Press ENTER Prompt to confirm the settings.

Select TAKEOFF page and set all data in accordance with

the runway analysis and airplane configuration for takeoff. At pilots discretion, select the LANDING page on the MCDU

and set the landing speeds for the takeoff weight in case ofimmediate return is necessary.

Select RADIO page 1/2 and insert assigned transpondercode and for LVTO using HGS set the ILS frequency for thedeparting runway on both NAV windows.

VSPEED READOUTS AND BUGSFour speeds are displayed prior to takeoff:

V1 .................1 ...................MAGENTA

VR.................R .................. CYAN

V2 .................2 ...................WHITE

VFS...............FS ...............GREEN


SPEED Selector Knob.......................................SET ...............LSP

At pilots discretion set the SPEED Selector knob to FMS orMANUAL.

IF FMS, set the departure speed on the DEP/APP speeds pageon the FMS.If MANUAL, set the speed VFSon the speed window.In case of Noise Abatement procedure set V2+10.

TOGA Button.................................................PRESS...............LSPVerify if the pitch cross bar on PFD agrees with the pitchindicated on PERF INIT page on MCDU.

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TRIM Panel............................... __SET/ZERO/ZERO .............. RSP

(Answered by LSP)

Set the PITCH trim according to load sheet and verify YAW andROLL trims to the neutral position.

Doors and Windows ..................................CLOSED ...LSP & RSP

(Answered by LSP/RSP)

Both pilots must verify that their respective cockpit window isclosed and the RSP should select MFD status page to check allairplane doors closed indications. It is recommended to assurethat escape slides are armed.Check the cockpit door securely closed.

Takeoff Briefing..................................COMPLETED ...LSP & RSP

The takeoff briefing should be performed by the PF and theleft seat pilot must state the Reject Takeoff procedures.

The briefing should describe the departure procedures, taxiout routes, power reductions, weather, terrain/MSA, noise

abatement procedures, low visibility procedures, inoperativeairplane components, runway in use/condition, returnalternate airports, NOTAMs and any required operationalprocedures that differ from the normal procedures. It isrecommended to perform the takeoff briefing before enginestart.

Red beacon.......................................................... ON .............. RSP

(Answered by LSP)

Electric Hydraulic Pump 3A............................... ON .............. RSP

Ground Equipment ......................... AS REQUIRED ...............LSP

If performing a push back assure that the ground equipment notused for this procedure is removed.

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Emergency/Parking Brake..............AS REQUIRED...............LSP

(Answered by LSP)

Verify if the Emergency/Parking brake is set in accordance withthe engine start procedures.

Steering Disengage Switch .........................PRESS ..............LSP

Verify the STEER OFF message displayed on the EICAS.

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ENGINE START

ENGINE START PROCEDURECHALLENGE ACTION

Associated START/STOP Selector............................START, thenRUN

Hold the START/STOP Selector at START position for at least2 seconds.

NOTE: During ground starts only, the transition of the cockpit

START/STOP switch from STOP to START must be less than30 seconds or the FADEC will prevent an engine start until theswitch is cycled through STOP.

Engine Parameters .....................................................MONITOR

Repeat the sequence for the other engine.

ABNORMAL ENGINE START INDICATIONS

Although FADEC provides automatic over-temperature protection andwill automatically abort the start in the event of a hot start, hot restartor hung start, the engine start must be manually aborted when:

No positive oil pressure indication within 10 seconds after N2speed starts to increase.

During engine start with tailwind, if a positive increase of N1 isnot indicated before starter cutout (50% N2). In this case theairplane should be repositioned prior to engine start tominimize tailwind effects.

For E170/175, no ITT indication within 30 seconds after fuel isapplied.

For E190/195, no ITT indication within 1 minute after fuel isapplied (15 seconds after fuel is re-applied).

ITT exceeds start limit (815C - Hot Start for E170/175 and

740C Hot Start for E190/195).

If oil pressure stabilizes below the engine limits.

N1 and/or N2 failing to accelerate to stable idle speed (HungStart).

An intermittent electrical pneumatic or starter malfunctionoccurs before the starter disengagement.

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