ae emb 145 panel review[1]

25 February 2006, William de Groh

The following pages depict the various instrument panels located in the cockpit of the Embraer E145 Regional

Jet. Along with these depictions are text box captions that describe the function of most of the buttons and

switches that control the various systems on the aircraft. Keep in mind that as aircraft modifications occur,

such as ADs, Service Bulletins, etc., the captions may become inaccurate or incomplete.

The captions are not all inclusive and are intended as a supplemental study aid to be used in conjunction with

the appropriate approved aircraft systems and operations manuals. Because space is limited for the captions

the use of acronyms and abbreviations is necessary. The table that follows lists the acronyms and

abbreviations used that may not be readily discernable by the reader.

Warning and Disclaimer

Every effort has been made to make this information as accurate as possible, but no warranty or fitness is

implied. The information provided is on an as is basis. The author shall have neither liability or

responsibility to any person or entity with respect to any loss or damages arising from the information

contained herein. - Captain Bill de Groh

Embraer E145 Cockpit Panels

Abbrev. Meaning

& and

_x Multiplier (4x = 4 times)

< Smaller/Less/Below

> Greater/More/Above

A Ampere

A/C Aircraft

A/I Anti-ice

ABV APU Bleed Valve

AC Alternating Current

AEO All Engines Operating

AGL Above Ground Level

AHRS Attitude Heading Reference

System

AMM Airplane Maint. Manual

Amp Ampere

AP Autopilot

Approx. Approximately

APU Auxiliary Power Unit

Auto Automatic

BACV Bleed Air Check Valve

BC Battery Contactor

BTC Bus Tie Contactor

CA Captain

CBV Cross Bleed Valve

Abbrev. Meaning

CCW Counter-clockwise

Cmd Command

Cmpt. Compartment

Com Communication

CVR Cockpit Voice Recorder

CW Clockwise

DAP Digital Audio Panel

DC Direct Current

DCP Display Control Panel

Decr. Decrease(s)

DFDR Digital Data Flight Recorder

EBC Essential Bus Contactor

EIC Essential Interconnection Contactor

EBV Engine Bleed Valve

ECS Environmental Control System

EDL Electrical Distribution Logic

EICAS Engine Indicating And Crew Alerting System

Elect. Electric(al)

ESU Electronic Sequence Unit

F/A or FA Flight Attendant

FADEC Full Authority Digital Electronic Control

FD Flight Director

FI Flight Idle

FO First Officer

May 2008 William de Groh


Abbrev. Meaning

Fpm Feet per minute

FSBY Forced Standby Mode

Ft Feet

Fwd Forward

GCU Generator Control Unit

GI Ground Idle

GMAP Ground Map Mode

GPC Ground Power Contactor

GPU Ground Power Unit

Grnd Ground

GS Glideslope

Hdg Heading

Horiz. Horizontal

hPa hectopascals

HSCU Horizontal Stabilizer Control Unit

HSV High Stage Valve

Hyd. Hydraulic

Hz Hertz (cycles per second)

ICU Interphone Control Unit

Incr. Increase(s)

Kts Knots

Lbs Pounds

LH Left Hand

LRN Long Range Navigation

Mag. Magnetic

Man. Manual

Max. Maximum

MFD Multi-Function Display

Mic. Microphone

Min. Minimum or Minute

Msg. Message

MSL Mean Sea Level

Nav Navigation

NiCad Nickel-Cadmium

Abbrev. Meaning

Nm Nautical mile

O2 Oxygen

OEI One engine inoperative

Pax. Passenger

PCA Power Control Actuator

PCU Power Control Unit

PFD Primary Flight Display

PRSV Pressure Regulating and Shutoff Valve

Psi Pounds per square inch

PSU Passenger Service Unit

PTT Push-To-Talk

RCP Radar Control Panel

Rcvr Receiver

Rdr Radar

REACT Rain Echo Attenuation Compensation Logic

Ref. Reference(d)

RH Right Hand

RTA Receiver/Transmitter/Antenna

Sec. Second(s)

SOV Shut Off Valve

SPS Stall Protection System

SRN Short Range Navigation

Sync. Synchronize(s)

Sys. System

TCS Touch Control Steering

Temp. Temperature

Tgt Target

TL Thrust Lever

TLA Thrust Lever Angle

V Volt

WX Weather radar mode

Xmtr Transmitter

YD Yaw damper



EMBRAER 145 RIGHT MAIN INSTRUMENT & GLARESHIELD PANELS

Pushed Calibrated Gain

Pulled Manual gain active &

VAR label displayed on PFD

Remote

Start/Stop/Reset for

chronograph

Quick Disconnect Button

Disconnects AP; AUTOPILOT voice msg self

canceled above 2500 ft with a valid radar

altimeter

Inhibits stick pusher

Disconnects all trim systems while pressed.

Switch on fwd side of

yoke disengages nose

wheel steering

Down Off

Center Hot Mic

Up - PTT

Pitch Trim with 3

sec. timer

Disengages AP

Capts has priority

Causes MFD to present PFD or

EICAS displays from on-side IC-600.

ADC selects cross-side ADC. ADC 1(2) on

PFD.

AHRS selects cross-side AHRS. ATT 1(2) &

MAG 1(2) on PFD.

SG selects cross-side symbol generator (IC-

600). ADC 1(2), ATT 1(2), MAG 1(2), & SG 1(2)

on PFD.

PSU O2 latches energized;

6 sec. timer

CLOSED Disables PSU

O2 latches. Also resets O2ON indicator & cabin signs

after system activation on

AUTO or MANUAL.

AUTO PSU O2 latches

energized & cabin signs on

when cabin altitude

> 14,000 ft.

MANUAL activates PSU

O2 latches at any altitude.

Range Select Buttons

In WX, REACT, & GMAP

modes 5 to 300 nm available.

In FP mode 5 to 1000 nm

available

TEST mode, auto set 100 nm

Rain Echo Attenuation Compensation Technique (REACT)

Pushed enables REACT

Avail in all mode except GMAP

Always selected when in TEST mode.

Calibrated Gain

Radar in Forced Standby Mode (FSBY) when A/C

on grnd and Radar Mode knob not set to OFF;

FSBY label displayed. FSBY inhibits the xmtr and

antenna scan; can override through the STAB

button.

REACT Automatic rcvr calibration to

compensate for attenuation losses. RCT label

displayed. A blue field indicates ranges where

further compensation not possible. Active in all

modes except GMAP. Tgts within blue field

cannot be calibrated & should be considered

dangerous.

OFF On-side controller slaved to cross-side

controller; SLV displayed on RCP.

SBY Standby mode. STBY label displayed.

WAIT label displayed during 40-100 sec. warm-up.

WX Weather detection mode. CA & FO RTA

settings alternate on each sweep, CAs on left

sweep & FOs on right. To get 100% duty factor

one Radar Control Panel must be set OFF. WX

label if rdr selected for display on MFD; otherwise

TX label

GMAP Ground map mode. GMAP label

displayed.

FP Flight Plan mode. Radar put in standby &

no radar data presented. A singular display of nav

data & a FLTPLN label displayed.

TEST Test pattern displayed with a TEST label.

Pressing cycles antenna

stabilization. When off

STAB on PFD and OFF

on RCP.

Used to invoke

stabilization Trim mode

On ground, after warm-

up, pressing 4x within 3

sec. inhibits FSBY

Selects Target Alert

Mode. Mode monitors for

red (level 3) or greater

beyond selected range &

+/- 7.5 of A/C hdg. TGT

label if target detected.

Min. target depth of 5

nm

TGT label with no target

Calibrated Gain

Radar operational if FP

mode selected.

Cycles between 120 or 60

azimuth sweep for on-side

AND cross-side displays.

Antenna Tilt +/- 15

Range indicators between +5

& -5 are expanded

Antenna beam width 7.9

Digital Audio Panel (DAP)

PAX reroutes audio signal from

crew mic to pax cabin when any

PTT is pressed.

EMER directly connects mic &

headphones to com/nav radios.

CA to Com/Nav 1, FO to Com/Nav

2.

DG AHRS hdg channel

operates as free non-

slaved gyro.

SLVD AHRS slaved to

flux valve.

Allows slewing of hdg

when AHRS not slaved to

mag hdg of flux valve.

Panel not present in

AH900 equipped a/c.

Radar

Control

Panel

(RCP)

Touch Control Steering (TCS)

While pressed allows manual

maneuvering without disengaging

the AP

When released syncs to new pitch

attitude & vertical mode &

maintains it.

Lateral control returned to

previously selected mode.

Pressing & releasing after GS

capture in APR mode with AP

engaged releasing AP will return to

ILS center beam.

Slide, with mask

stowed, tests the mask.

Flow indicator turns

yellow momentarily &

OXY ON flag appears

Slide, with mask not

stowed & left door

closed, shuts off O2 to

the mask.N O2/Air mixture

based on cabin

altitude; pure O2 above

33,000 ft.

100% - Pure O2 at all

altitudes. Must be

selected with

EMERGENCY position

for protective breathing

Rotated CW to

EMERGENCY position

supplies 100% O2 under

positive pressure

Pressed, tests regulator

demand mechanism

Primary Flight

Display (PFD)

[Avionic Switched

DC Bus]

Switch altimeter ref.

between Inches and HPa.

Standard altimeter setting

button

Clock

Gasper vent

Interior Lights

Control Panel

Foot Warmer

Valve

Avionic Switched

DC Bus

PFD comparison montiorsHDG > 6 for a/c roll < 6

or >12 for a/c roll > 6ROL >6PIT >5ATT if both ROL and PIT setALT 200 ft or more IAS > 5 ktsLOC .> 1/2 dot (below 1200 ft.)GS .> 2/3 do (below 1200 ft.)ILS if both LOC and GS set

Vertical CDI Scaling per dot

For CN: GS = 0.35

For FMS: ENR = 750

TERM = 0.35

APPR = 0.35

VNAV = 250

Horizontal CDI Scaling per dot

For CN: LOC = 1.25

VOR = 5

For FMS: ENR = 2.5 nm

TERM = 1.0 (0.5 nm)

APPR = 0.15 nm



EMBRAER 145 CENTER MAIN INSTRUMENT & GLARESHIELD PANELS

Cancels LANDING GEAR voice

msg. in case of Radio Altimeter loss

only when flaps < 22

Striped bar in button when pressed

Striped bar extinguishes if TLs

advanced or flaps set above 22 , or

gear down & locked

LANDING GEAR voice msg activated when:

Flaps < 22, one TL < 45 (59 if OEI), and

Radio Altitude < 1200 ft. Can be canceled.

Flaps set at 22, one TL < 45 (59 if OEI), and

Radio Altitude < 1200 ft. Cannot be canceled.

Flaps set at 45. Cannot be canceled.

Inhibits EGPWS when approaching

airports not covered by EGPWS

database thus avoiding unwanted

terrain alerts.


ON Activates ELT

ARM Allows automatic

activation

TEST/RESET function

enabled by pressing ON,

waiting 1 sec. then

pressing ARM

RESET function

deactivates ELT after

manual or auto activation

Flashing ELT alert

light indicates ELT

transmitting

Standby Attitude Indicator

Pull to cage & rotate to

adjust miniature airplane

Power warning flag

Power off

Caged

Open motor winding

Loss of power

Essential DC Bus 2

Standby Altimeter

Standby Airspeed Indicator

Multi Function

Display (MFD)

Engine Indication & Crew Alerting System (EICAS)

Optional Integrated Standby

Instrument System (ISIS)

Replaces the three

electromechanical standby

instruments with a single LCD

screen

Powered from Essential Bus 2

CAGE button resets attitude

only

STD button sets standard

barometer setting

The + or keys adjust

brightness

Rotary knob allows altimeter

setting

Indicates when

emergency/parking

brake is applied

Cycles between full

rose HSI & sector

format on PFD

In sector format WX

radar can be displayed

Cycles between ground

speed and time-to-go.

First press enters

Elapsed Timer Mode

Start/Stop/Reset

Cycles between on-side

VOR/LOC SRN source

(green) or cross-side

VOR/LOC SRN source

(yellow)

Cycles between on-side

FMS LRN source

(magenta) and cross-

side FMS LRN source

(yellow)

OFF Associated bearing

pointer sources disabled

NAV Selects associated VOR

as bearing pointer source

ADF Selects associated ADF


FMS Selects associated FMS


Master Warning Button

Rotation allows setting

Radio Altimeter decision

height

On grnd, pressing activates

IC-600 first level IBIT test. If

held > 6 sec. activates IC-

600 second level IBIT test.

EICAS test commanded from

CAs panel only.

In flight, pressing activates

Radio Altimeter Test

TEST displayed

100 +/- 10 ft

Rotation allows pilot to

scroll through EICAS

messages if display limit

of 15 exceeded.

Rotation allows setting

airspeed bug values

Displays FD bars

Bank angle reduced from

27 to 14 in HDG mode .

Auto selected climbing >

25,000 ft & canceled <

24,750 ft in HDG mode.

Annunciated only in HDG

Select mode

Allows crs selection

Pressing synchronizes

selected course to VOR

bearing

Allows hdg selection

Pressing synchronizes

hdg bug to current hdg

Hdg Hold (ROL) holds

present hdg when

selected

Hdg Select (HDG)

follows hdg bug

Allows CAs or FOs FD

to control the AP

Engages AP & YD

Pressed again

disengages AP but

keeps YD

Couples FD to nav

source selected on

flying pilots DCP.

VOR/LOC if NAV

selected and LNAV if

FMS selected

Same as NAV but

with higher gain.

Also enable GS

Mode.

Display Control

Panel (DCP)

Engages YD

Pressing again disengages

both AP & YD

Speed Hold Mode

Flight Level Change

Altitude Hold Mode

Vertical Speed Hold Mode

Setting

Knobs

Flight Level Change Mode

Climb

240 kts / 0 to 10,000 ft

240 kts to 270 kts / 10,000 to 12,000 ft

270 kts / 12,000 to 17,377 ft

0.56M / 17,377 to 37,000 ft

Descend

-2,000 fpm / 37,000 to 12,000 ft

-2,000 to -1,000 fpm / 12,000 to 10,000 ft

-1,000 fpm / less than 10,000 ft

Backup Ess Bus

Avionic Switched

DC Bus

Some EICAS messages inhibited

Takeoff: V1-15 to 400 RA

Landing: 200 RA to 3 sec. after W-on-W FMS Roll Cmds for Leg-to-Leg changes

27 bank up to 20K

Dec. linearly above 20K up to 32K

15 bank above 32K

Roll rate limited to 3/sec

FMS Roll Cmds for Direct To changes

30 bank up to 20K

Dec. linearly above 20K up to 32K

20 bank above 32K

Roll rate limited to 3/sec



EMBRAER 145 CENTER PEDESTAL

Illuminates when

disconnection

mechanism activated

Disconnects CAs

elevator control from

FOs

CAs side has all AP

servos & stick pusher

Cannot be reset in flight

Disconnects CAs

aileron control from FOs

FOs side has roll trim

actuator & artificial feel

unit

Cannot be reset in flight

Checks takeoff configuration warning by

simulating TLs advanced

If ok, TAKEOFF OK voice message

If fail, TAKEOFF ___ voice message & NO

TAKEOFF CONFIG EICAS msg

FLAPS

SPOILERS

TRIM

BRAKES

Illuminates when

disconnection

mechanism activated

Mechanical gust lock secures only the elevator

Electromechanical gust lock does the same thing but

uses a solenoid and locking pins installed in the

horizontal stabilizer. Powered by DC Bus 2 &

incorporates an amber indication light on the glareshield.

Cmds outboard spoiler

panels to open when:

TLA of both

engines < 50

Flaps < 13

No intermediate

positions

Electrically controlled

thru DC Bus 1 & 2

Hydraulically actuated

Thrust Reversers have

3 locking systems. The

Primary & Secondary

are electrically

controlled &

hydraulically actuated.

The third lock is

completely electric.

Loss of electric power

latches locks closed

Pulling actuates

emergency brakes (no

anti-skid)

Pull & rotate to set

parking brake

Always have toe

brakes applied when

setting or releasing to

prevent hydraulic fluid

transfer

All 4 brakes supplied

by Hyd Sys 2

proportional to handle

displacement with no

protections

Electrically actuated &

controlled

DC Bus 1 & 2

If one channel fails,

remaining motor can

drive flaps at half speed

3 asymmetrical limit

disables system for

duration of flight

MAX max. takeoff

rating mode at any time

THRUST SET

FADEC controls engine

to achieve N1 target

IDLE GI~ 64% N2, FI~

68% N2

MAX REV max.

reverse thrust. Doors

cmdd open when TLs

at soft detent (TLA 14)

If OEI or one reverser

not deployed FADEC

will only cmd reverse

from good engine if TL

requesting reverse

and OEI TL set to

IDLEThrust Lever

Friction Knob

Joystick controls

MFD designator

With control column held full back, momentary push

actuates SPS test (stick shaker, clacker, & stick pusher)

TEST button illuminated after an unsuccessful test or if

system has not been tested.

TEST button inhibited inflight till 30 sec. after landing,

above 70 KIAS, or with gear not downlocked.

Ice compensation of SPS inhibited for 5 min. after takeoff.

Ice compensation reset if:

airborne & flaps set to 45. SPS ICE SPEED msg

remains,or

on ground after pressing TEST button. SPS ICE

SPEED msg cleared.

Cuts out SPS channel

1 or 2 in case of failure

Striped bar in button

when pressed

Thrust Mode select buttons

(no ATTCS)

CON thrust if one of the following:

>300 ft AFL & gear not locked down, or

>1700 ft AFL

Limited to OEI only

CLB or CRZ thrust if one of the following:

>500 ft AFL, gear not locked down, AEO, or

>1700 ft AFL and AEO

TO thrust

T/O-1 for the EMB 145

T/O RSV for the EMB 135/140

Pedal brking

Hyd Sys 1 supplies outbd brakes

Hyd Sys 2 supples inbd brakes

Anit-skid protection > 10 knots

wheel speed

Locked wheel protection through

anti-skid system > 30 knots wheel

speed

Touchdown protection allows

braking 3 seconds after

touchdown, or when wheel speed

> 50 knots.

Pusher inhibited

On grnd (except for test)

Below 0.5 G

While Quick Disconnect

button pressed

< 200 ft if RA failed

Any Cutout button

pressed

> 200 knots

At least 1 channel inop

Inhibition Logic

Takeoff

Active > V1-15

Deactive. RA > 400 ft,

or < 60 kts, or > 1 min.

Landing

Valid < 200 ft

Deactve. WOW > 3

sec., or > 1 min.



EMBRAER 145 AFT CENTER PEDESTAL

ARINC Communications And

Reporting System (ACARS)

Printer

Actuates roll trim by

repositioning neutral

position of aileron

command

Actuates yaw trim

3 sec. timer in case of

trim knob failure

Cuts out (pressed) or

enables (released)

HSCU Main or Backup

Pitch Trim systems

Striped bar in button

when pressed

Actuates pitch trim

through the HSCU

backup channel

Must be in DN position in

AUTO mode

In MAN Mode:

Controls pneumatic

outflow valve by

metering vacuum

pressure to that valve

-1500 fpm to +2500 fpm

in MAN mode

On (pressed)

Dumps cabin up to

14,500 ft +/-500 ft

ON inscription when

pressed

Inhibited in MAN mode

Auto mode (released) or

Manual mode (pressed)

MAN inscription

illuminated when pressed

Pitch control wheel

inhibited if any Vertical

Mode selected in FD

Manually controls roll

attitude when AP

engaged

Control Display Unit (CDU) of

Universal UNS-1K Flight Management

System (FMS)

Landing Gear Freefall Compartment

On floor between co-pilots seat and control pedestal

Electrical Override Switch

NORMAL Extension/retraction controlled by LGEU

DOORS Bypasses LGEU to open nose landing

gear doors

GEAR DOORS Bypasses LGEU extending landing

gear while keeping nose landing gear doors open.

Free-Fall Lever

Initial movement operates the free fall selector valve

relieving hydraulic pressure and connecting the lines

to the return. Further movement mechanically

unlocks the landing gear uplocks allowing the gear to

free-fall to the down and locked position.



Connects (pressed) or disconnects

(released) the GPU to/from the

electrical system.

GPU AVAIL inscription illuminates

when operating GPU is physically

connected to aircraft; does not indicate

good power.

Inscription goes out when button

pressed & GPU connected to electrical

network. Priority over alll batts & gens.

Striped bar in button when pressed.

Verify 26.0 - 29.0 V before selecting.

Erases data only on the ground with

parking brake set. Only the

manufacturer can recover the erased

data.

EMBRAER 145 OVERHEAD CHANNEL A

ELEC EMERG. Loss of all generators in flight. The batteries supply the Central & Essential Buses, sharing the load & not being

charged. The Inverter, Shed and DC Buses not energized.

ELEC EMERG. ABNORMAL The EDL configured for an electrical emergency when not required. The generator supplied DC

Buses are isolated from the battery supplied Central & Essential Buses & the batteries are not being charged.

ELEC ESS XFER FAIL The EDL failed to configure for an electrical emergency when required. DC Bus 1 and/or DC Bus 2 are

not isolated from the batteries & the batteries are not being charged.Jack for a 600 ohm headphone to monitor

audio signals & tones.

2 sec. 800 Hz tone for successful CVR

test

3 sec. 400 Hz tone for successful CVR

erase


(released) the 28 vDC, 400 Amp engine-

driven generators to/from respective DC

Bus

Gens online when N2 > 56.4%

Cycling resets GCU if generator is

running.

If current > 400 A, GEN 1 (2, 3, 4) OVLD

msg.

Striped bar in button when released.


(released), 28 vDC 400 Amp, APU Starter-

Generator when APU rotor speed > 95% +

7 sec.

BATT 2 used to start APU


OFF BC kept open disconnecting

battery from electrical system.

AUTO BC controlled by EDL

Two 24vDC, 44 amp-hour NiCad

batteries, located in battery cmpt. (Nose

left side).

BATT 2 supples power for APU starting,

while BATT 1 isolated to provide

stabilized power to voltage transient

sensitive equipment.

Both BCs open if GPU connected to

system

During an Electrical Emergency both

batteries can supply Essential Buses for

40 min., which includes 3 APU starts.

If batt > 70C, BATT 1 (2) OVTEMP msg.

OVRD Closes Shed Bus contactors

while on ground with at least one

generator on line.

AUTO EDL controls Shed Bus

contactors.

OFF Opens Shed Bus contactors

manually regardless of EDL.

Connects (pressed) or disconnects (released) the com/nav supplied by

Avionics Switched Buses.

Allows prevention of undesirable voltage transients during APU battery starts on

the ground.


On (pressed), overrides auto transfer

to electrical emergency configuration &

ensures batteries powering only

Essential Buses regardless of EDL.

Isolates batteries from DC Buses.

(EBC 1 & 2, and EIC closed, BC1 and

BTC 2 open).

Auto (released), power contactors

operate automatically according to

EDL. (EBC 1 & 2, and EIC open, BC1

and BTC 2 closed).

Striped bar in button when pressed.

OVRD BTCs kept closed regardless

of EDL provided no overcurrent

detected by one of 5 GCUs.

AUTO BTCs controlled by EDL.

OFF Opens BTCs regardless of EDL.


(released) the 250 VA/400 Hz Static

inverter to/from the system.

Inverter supplied from DC Bus 1 &

provides 115 vAC to 115 vAC Bus.

115 VAC BUS OFF msg. if Bus

deenergized

Powers TCAS II & GPWS


ON Emergency lights ON using the 4 dedicated batteries; 15 min. duration; batteries not charging - EMER LT NOT ARMEDOFF Emergency lights turned off if EMER LTS button on F/A Panel in NORM; batteries not being charged - EMER LT NOT ARMED.(Switch that turns on the lights is the only switch that can turn them off)

ARM Emergency lights off & batteries being charged; lights illuminate automatically in Elec. Emerg.


(released) the Backup Battery to/from

the electrical system.

24 vDC, 5A lead acid battery, in fwd

avionic cmpt. in front of FO.

Backup Batter y charged when

button pressed with BATT 1 in AUTO

BKUP BATT OFF BUS msg when

button released.

Supplies Backup Hot Bus, providing

stablized power for the GCU's

protective function in case of a short-

circuit or near zero system voltage.

Ground Service Bus is energized when

BATT 1 & 2 OFF (BC1 & BC2 open)

and GPU AVAIL inscription in GPU

button (GPC open). Cockpit dome,

courtesy, galley, cabin, lav, bagg, &

service cmpt. lights

Tests integrity of CVR

Green STATUS LED illuminates for

1 sec. if test is good

DC Bus 2, 2 hr recording, 5g switch



Illuminates red upon fire detection

Pulling will send close cmd to:

Hyd. Pump SOV

Bleed Air SOV

Engine Intake Lip Anti-ice SOV

Fuel SOV (on Hot Bus).

Remember H.A.L.F.

Rotate CCW fires bottle A & CW fires

bottle B

Fire bell can be canceled but visual

warning cannot as long as fire signal

exists.

Selects which electric fuel pump will be

operating continuously for that engine

Remaining pumps of associated side are

kept in auto standby

If fuel pressure < 6.5 psi remaining two

pumps come on line & will cycle with

inoperative pump causing clicking in relay

box.

FUEL 1 (2) LOW LEVEL

Fuel remaining ranges from 463 to 584

lbs.

FUEL IMBALANCE

Comes on at 800 lbs difference

Goes off at 100 lbs difference

EMBRAER 145 OVERHEAD CHANNEL B

Fuel tank temperature taken from left tank

only & displayed on MFD, FUEL page.

FUEL TANK LO TEMP msg. indicates fuel

temp. inside left tank is < -40C

E1 (2) FUEL LO TEMP msg. indicates engine

fuel temp. (leaving FCOC) is < 5C.

Pressure refueling to full leaves 7.9 U.S.

gallons below fuel tank capacity; must fuel

over wing to get that last 7.9 U.S. gallons.

To de-fuel left tank set XFEED to LOW 2 and

Tank 1 - ON with de-fuel SOV open

LOW 1 opens cross-feed valve & shuts off

left selected electric fuel pump

OFF closes cross-feed valve & returns

electric fuel pump to normal operation

LOW 2 opens cross-feed valve & shuts off

right selected electric fuel pump

To cross-feed select tank with lower fuel

Switch powered by Ess DC Bus 2

ON Energizes selected pump

OFF De-energizes selected pump

Fuel Pump A on associated Essential Bus

Fuel Pump B on cross-side Essential Bus

Fuel Pump C on associated DC Bus

Same as CABIN button

except on F/As Call Panels:

EMER

PILOT

Allows interphone com

between FA and pilots.

Generates cabin chime

On FAs Call Panels:

Striped bar when button

when pressed

PILOTAllows interphone com between pilots and

FA in case of normal mode failure

Illuminated CABIN and CAB EMER buttons

on ICU, and PILOT and EMER PILOT

annunciators on Attendants Call Panel


Interphone Control Unit (ICU)

Generates a cabin chime to call FA

Turns on or off the associated lights

DFDR begins recording when RED

BCN switch in ON or A/C is airborne .



EMBRAER 145 OVERHEAD CHANNEL C

Enabled on grnd only with TLA < 50

1st press enables T/O Mode setting

2nd press REF TO TEMP

3rd press REF A-ICE

4th press stores values. Data accepted if

REF TO TEMP within +/-10C & both

engines running

STOP Cmds FADEC to shut engine

down provided TLA is IDLE

RUN Allows normal engine operations

START Initiates engine start cycle, and

automatically switches FADEC from the

FADEC that had the last successful engine

start. If held > 3 sec. knob becomes

inoperative. In this case select STOP and

reset the FADEC to reset knob

T/O Mode: DEC ALT T/O-1,

INC T/O-1 or T/O (135/140 only)

REF TO TEMP: DEC decreases temp.

setting, INC increases temp. setting

REF A-ICE: DEC OFF, INC - ON

OFF De-energizes ignition system

AUTO Active FADECs control ignition

system automatically

One channel for grnd start (14% N2)

Both channels for airstart (10% N2)

Auto-relight (above 53% N2)

ON Cmds FADECs to continuously

activate both ignition channels; A & B.

First flt of day

Cold eng. starts SAT or oil < 5C

External air or Crossbleed start

Contam.runway TO AND < 10C.

Moderate or > turb. or heavy precip.

RESET Resets FADEC & clears faults

ALTN Alternates FADEC in control

Inoperative if held > 3 sec.

OFF De-energizes FADEC, closes APU

Fuel Feed SOV in wing stub (APU FUEL

SOV CLSD EICAS msg) & closes APU

Main Fuel Solenoid Valve (at APU)

R.emoves APU indications & alarms when

RPM < 10%, cmds APU shutdown.

ON Energizes FADEC (Ess DC Bus 2 or

HOT Bus 1), opens APU Fuel Feed SOV,

enables APU indications & alarms on

EICAS. FADEC performs self-test.

START Initiates start cycle

APU Normal Shutdown

Sends stop request to FADEC and closes the

APU Main Fuel Solenoid Valve (at the APU).

Sends stop request to FADEC, and

Closes APU Fuel Feed SOV in wing stub

(APU FUEL SOV CLSD EICAS msg) & closes

APU Main Fuel Solenoid Valve (at APU)


APU start cycle:

3% (0% airborne): ignition energized & Main

Fuel Solenoid Valve opens

50%: Starter de-energized

70%: ignition exciter de-energized

95%+7sec: Max Fuel Solenoid Valve

energized, pneumatic & electrical power

available

If no EGT rise then 1 auto restart (swing start):

starter de-energized at 20% & re-energized at

5%.

Button illuminated if smoke detected in

baggage compartment

When pressed

Discharges both bottles; the high rate &

metered discharge bottles

Deactivates baggage compartment fans

(if not previously deactivated by smoke

detection)

50 minutes of protection

Causes APU Normal Shutdown, and

closes APU Fuel Feed SOV in wing stub

(APU FUEL SOV CLSD EICAS msg) &

closes APU Main Fuel Solenoid Valve (at

APU)

Discharges APU fire bottle

Does NOT illuminate

30 sec delay, per EPC, before pressing

Permits testing the fire detection system

On grnd, if pressed & held > 10 sec. APU

auto shut down in the same manner as if

the FUEL SHUTOFF button was pressed.

If necessary to repeat fire test, wait at least

6 sec.

In the case of APU fire detection, the APU

will NOT auto shutdown in flight but will

auto shutdown if A/C on the ground.

Class C baggage compartment

Two cargo extinguisher bottles located in

rear Electrical Compartment

Two smoke detectors Maintenance must

reset

Sight glass in lavatory

Turns on/off both taxi lights & nose

landing light, respectively

Taxi & nose landing lights automatically

extinguished when nose gear not down &

locked, regardless of switch position

Shed Bus 2 must be energized (OVRD

with < 3 generators on line)

Turns on/off wing landing lights

Abnormal APU Shutdown:

In Flight: Overspeed, underspeed, loss of

speed data, failure to start, accelerate, or

light, external short, or FADEC failure or

loss of signal.

On Ground: Fire (APU FIRE aural warning

of 10 sec. or more), EGT over-temperature,

Loss of EGT, high oil temperature, low oil

pressure, oil pressure switch short.



EMBRAER 145 OVERHEAD CHANNEL D

Illuminates red upon fire detection

Pulling will send close cmd to:

Hyd. Pump SOV

Bleed Air SOV

Engine Intake Lip Anti-ice SOV

Fuel SOV.

Remember H.A.L.F.

Rotate CCW fires bottle A & CW fires

bottle B

Fire bell can be canceled but visual

warning cannot as long as fire signal

exists.

Enables (pressed) or disables

(released) associated hydraulic

system pressure to both aileron

actuators.

Striped bar in button when released

Enables (pressed) or disables

(released) associated rudder hydraulic

actuator.


Automatic Rudder Shutoff Through Speed Switch

Rudder limiter for high speed

Rudder Sys 1 auto shutoff > 135 kts to reduce

rudder authority at high speed

If Sys 2 fails Sys 1 comes back on line

automatically with EICAS message

RUDDER OVERBOOST if neither Sys shuts off

> 135 kts

Rudder Hardover Protection (for low speed)

Both Sys 1 & 2 auto shutoff

Force on any pedal > 130 lbs, and

Rudder deflected > 5 to opposite side, and

Both engines running (N2 > 56.4%)

Inhibited at higher speeds due to speed switch

logic that reduces rudder authority. Rudder

deflection will not achieve 5

Inhibited with OEI operation

Priority Valve

Only on Hyd Sys 1

Priority valve closes during ldg

gear operation with only electric

hyd. pump supplying system, to

isolate ldg. gear giving priority to

the flight controls.

Accumulator

Emerg. Brake

Accumulator

Closes (pressed) or opens (released)

engine-driven Hyd. Pump SOV

Hyd. Pump continues to run if engine

running


Hyd. Pump driven by engine accessory

gear box

Provides 3000 + 100 psi @ 9.2 gal/min

E1 (2) HYD PUMP FAIL msg < 1600

psi or N2 < 56.4%

HYD 1 (2) LO QTY msg if reservoir < 1

liter

Reservoir capacity 6 liters

24 hr parking brake or 6 full

emerg. brake applications

OFF Electric Hyd. Pump off

ON Electric Hyd. Pump on. Provides

2900 + 100 psi @ 1 gal/min

AUTO Electric Hyd. Pump in standby

ready to come on line if engine driven

pump outlet pressure < 1600 psi or N2 <

56.4%

HYD SYS 1 (2) FAIL msg if hyd.

pressure < 1300 psi

Turns signs on or off with a

chime

Both signs are automatically

activated when pax O2dispensing units open

Control cockpit

dome lights at a

fixed intensity

Control logo lights on

underside of

horizontal stabilizer

An accumulator is basically a

hydraulic battery storing

hydraulic energy & providing

surge protection.



EMBRAER 145 OVERHEAD CHANNEL E

Off (released) or permits (pressed)

automatic activation of engine lip anti-icing

OPEN inscriptions indicates engine lip anti-

ice valve open


Source is a valve upstream of HSV with no

temperature control (i.e. EBVs can be

closed & still operate)

Can be open on the grnd without limitation

On (pressed) or off (released)


Defog mode if no ice detected - maintains

windshield at 26 C. If ice cond. anti-ice

mode holds windshield at 43 C

3 sensors, 1 temp control, 1 overheat

protection, 1 spare

Should be off when OAT > 10C on grnd

ENG Inlet A/I valve open with engine

running. On grnd. with wheel speed > 25 kts

an ICE CONDITION will open WING and

TAIL A/I valves.

AUTO Allows automatic operation of

bleed air anti-ice system. On grnd. no A/I

valves open. But at wheel speeds > 25 kts

an ICE CONDITION will open all A/I valves

(ENG, WING, & TAIL)

ALL Turns on entire bleed air anti-ice

system in flight regardless of ice detection.

On grnd inlet A/I valve open & when wheel

speed > 25 kts the WING and TAIL A/I

valves open, regardless of ice condition.

Pressed- left pack automatically controlled

between 18C and 29C by Digital

Temperature Controller.

Pull for manual operation

On (pressed) or off (released)

Controls both recirc fans. On grnd

during hot soak days must be OFF;

during cold soak days must be ON


Pressed- right pack automatically

controlled between 18C and 29C by

Digital Temperature Controller

Pull for manual operation

ATTD Control transferred to FA Panel

where green ON light illuminates.

Off (released) or selects auto mode

(pressed) of wing and/or horizontal stabilizer

A/I valves. L pneumatic supplies horizontal.

OPEN inscription means valves open with

system cmdd open or at least one valve

open with system not cmdd open.


Off (released) or auto mode (pressed)


Pitot 1/2, Pitot/Static 3, AOA 1/2, ADS Static

Ports 1,2,3,4, & Press. Static Ports 1/2 are

heated with at least one engine N2 > 56.4%

Separate logic ensures Pitot/Static 3 & Press.

Sys. Static Port 2 heated in any flight condition

TAT 1 & 2 heat when TLs > 65 TLA (~78.5 to

82.5% N1) and assoc. engine A/I system on,

OR anytime inflight.

EICAS msg inhibited during takeoff & landing.

Permits testing wing, horizontal stabilizer,

and engine anti-ice valves by simulating an

ice condition on ice detectors 1 & 2.

Opens (pressed) or closes (released) the

Pack Pressure Regulating and SOV (PRSOV)


On grnd, with main door open & pack <

227C PRSOV operates in high mode, other

times in low mode

PACK 1 closes with A/I on below 24,600 ft

provided PACK 2 operating

Max thrust (takeoffs & go-arounds) with EBVs

open, Pack Valves automatically close by

FADEC when:

OEI up to 9700 MSL & TAT >19C at

S.L. decreasing to -5C at 9700 MSL

AEO up to 1700 AGL & TAT >19C

decreasing to -5C at 9700 MSL

Must reset Pack Valves after auto shutdown

If both Pack Valves closed in flight the ram

air valves open & recirculation fans auto

shutdown.

On the ground the ram air valves are always

closed, regardless of Pack Valve position.

On (pressed) or off (released) AIRBORNE

ONLY

Gasper ON with DC Bus 2 energized on grnd

regardless of button position


Supplies gaspers, and ventilation for the O2cyl. cmpt., relay boxes, and rear elect. cmpt.

CLOSED Closes CBV

OPEN Opens CBV (CROSS BLD OPEN)

AUTO Automatic operation of CBV

Electrically controlled, pneumatically

actuated

EBV (PRSOV) open (pressed) only when

bleed air demanded or closed (released).

LEAK inscription indicates duct leakage.

Engine inlet lip A/I taken upstream of HSV

HSV (14th stage) open during low thrust,

crossbleed starts, and A/I operations

9th stage air joins 14th stage, both with

BACVs, then thru precooler upstream of EBV

EBV closed by Fire Handle or automatically

with intense hot air leak (BLD VLV CLOSED)

Used for engine start, ECS, pressurization,

& ice protection

Opens (pressed) or closes (released) ABV.


OPEN inscription indicates ABV in open

position

APU bleed air not sufficient for A/I

Auto closes if LH EBV or RH EBV with CBV

are open to prevent reverse flow. BACV

downstream of ABV for same purpose.

Electrically controlled & pneumatically

actuated

BLEED TEMP on ECS page of MFD is

taken downstream of precooler.

LOW 80 strokes/min

HI 140 strokes/min

TIMER Intermittent operation, 2 strokes at high

speed with 8 sec. delay

Dry windshield protection parks blades until knob

cycled to OFF to reset.

Maximum speed for operation - 160 KIAS



Pressing allows Data

Acquisition Unit (DAU) Channel

B to supply both IC-600

Striped bar in button when

pressed

Radio Management Unit (RMU)

Tuning Backup Control Head (TBCH)

Allows alternative means of tuning Com

2 and Nav 2

NORM RMU tuning available

EMERG tuning through RMU

inhibited

EMBRAER 145 FORWARD CENTER PEDESTAL

DAU 1: Forward aircraft & engine 1 parameters.

Ch A: Ess DC Bus 1 & Backup Ess Bus (default)

Ch B: DC Bus 1

DAU 2: Aft aircraft & engine 2 parameters.

Ch A: Ess DC Bus 2 & Backup Ess Bus (default)

Ch B: DC Bus 2

First press: Splits the NAV window into

two windows. Top window displays

active VOR frequency. The lower

window, with the DME Label, displays

the active DME frequency in VHF

format. An H (DME Hold) is displayed

in the DME window and on the PFD to

show DME not paired with active

VOR/ILS freq. The DME may then be

tuned directly by pressing the LSK

beside the DME window.

Second press: Displays the TACAN

channel format and will allow tuning to

the DME portion of any TACAN station.

Third press: Reverts NAV window to

normal DME operation.

Activates internal self-test of component

selected with yellow cursor box.

COM transceiver Hold button 2 sec.

DME, ATC, and ADF Hold for 5 to 7 sec.

NAV (VOR/ILS) Hold for 20 sec.


ae emb 145 panel review[1]

Documents

fa flight attendantfadec

engine inoperativepax

various systems

text box captions

aircraft modifications

service bulletins

x multiplier

use of acronyms