Embraer E145 Cockpit Panels

Embraer E145 Cockpit Panels
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
Abbrev.
Meaning
Abbrev.
Meaning
&
and
CCW
Counter-clockwise
_x
Multiplier (4x = 4 times)
Cmd
Command
Cmpt.
Compartment
<
Smaller/Less/Below
Com
Communication
>
Greater/More/Above
CVR
Cockpit Voice Recorder
A
Ampere
CW
Clockwise
A/C
Aircraft
DAP
Digital Audio Panel
A/I
Anti-ice
DC
Direct Current
ABV
APU Bleed Valve
DCP
Display Control Panel
AC
Alternating Current
Decr.
Decrease(s)
DFDR
Digital Data Flight Recorder
AEO
All Engines Operating
EBC
Essential Bus Contactor
AGL
Above Ground Level
EIC
Essential Interconnection Contactor
AHRS
Attitude Heading Reference
System
EBV
Engine Bleed Valve
ECS
Environmental Control System
AMM
Airplane Maint. Manual
EDL
Electrical Distribution Logic
Amp
Ampere
EICAS
Engine Indicating And Crew Alerting
System
AP
Autopilot
Elect.
Electric(al)
Approx.
Approximately
ESU
Electronic Sequence Unit
APU
Auxiliary Power Unit
F/A or FA
Flight Attendant
Auto
Automatic
FADEC
Full Authority Digital Electronic Control
BACV
Bleed Air Check Valve
FD
Flight Director
BC
Battery Contactor
FI
Flight Idle
BTC
Bus Tie Contactor
FO
First Officer
CA
Captain
CBV
Cross Bleed Valve
25 February
2006, William
May
2008 William
de Grohde Groh
Abbrev.
Meaning
Abbrev.
Meaning
Fpm
Feet per minute
Nm
Nautical mile
FSBY
Forced Standby Mode
O2
Oxygen
Ft
Feet
OEI
One engine inoperative
Fwd
Forward
Pax.
Passenger
GCU
Generator Control Unit
PCA
Power Control Actuator
GI
Ground Idle
PCU
Power Control Unit
GMAP
Ground Map Mode
PFD
Primary Flight Display
GPC
Ground Power Contactor
PRSV
Pressure Regulating and Shutoff Valve
GPU
Ground Power Unit
Psi
Pounds per square inch
Grnd
Ground
PSU
Passenger Service Unit
GS
Glideslope
PTT
Push-To-Talk
Hdg
Heading
RCP
Radar Control Panel
Horiz.
Horizontal
Rcvr
Receiver
hPa
hectopascals
Rdr
Radar
HSCU
Horizontal Stabilizer Control
Unit
REACT
Rain Echo Attenuation Compensation
Logic
HSV
High Stage Valve
Ref.
Reference(d)
Hyd.
Hydraulic
RH
Right Hand
Hz
Hertz (cycles per second)
RTA
Receiver/Transmitter/Antenna
ICU
Interphone Control Unit
Sec.
Second(s)
Incr.
Increase(s)
SOV
Shut Off Valve
Kts
Knots
SPS
Stall Protection System
Lbs
Pounds
SRN
Short Range Navigation
LH
Left Hand
Sync.
Synchronize(s)
LRN
Long Range Navigation
Sys.
System
Mag.
Magnetic
TCS
Touch Control Steering
Man.
Manual
Temp.
Temperature
Max.
Maximum
Tgt
Target
MFD
Multi-Function Display
TL
Thrust Lever
Mic.
Microphone
TLA
Thrust Lever Angle
Min.
Minimum or Minute
V
Volt
Msg.
Message
WX
Weather radar mode
MSL
Mean Sea Level
Xmtr
Transmitter
Nav
Navigation
YD
Yaw damper
NiCad
Nickel-Cadmium
25 February
2006, William
May
2008 William
de Grohde Groh
EMBRAER 145 RIGHT MAIN INSTRUMENT & GLARESHIELD PANELS
Rain Echo Attenuation Compensation Technique (REACT)
•Pressing cycles antenna
stabilization. When off
STAB on PFD and OFF
on RCP.
•Pushed enables REACT
•Avail in all mode except GMAP
•Always selected when in TEST mode.
•Used to invoke
stabilization Trim mode
•Calibrated Gain
Range Select Buttons
•In WX, REACT, & GMAP
modes 5 to 300 nm available.
•In FP mode 5 to 1000 nm
available
•On ground, after warmup, pressing 4x within 3
sec. inhibits FSBY
Radar
Control
Panel
(RCP)
•Selects Target Alert
Mode. Mode monitors for
red (level 3) or greater
beyond selected range &
+/- 7.5º of A/C hdg. TGT
label if target detected.
•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.
•Min. target depth of 5
nm
•TGT label with no target
•Calibrated Gain
•Radar operational if FP
mode selected.
•TEST mode, auto set 100 nm
•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.
Cycles between 120º or 60º
azimuth sweep for on-side
AND cross-side displays.
•Pushed – Calibrated Gain
•WX – Weather detection mode. CA & FO RTA
settings alternate on each sweep, CA’s on left
sweep & FO’s 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
•Pulled – Manual gain active &
VAR label displayed on PFD
Interior Lights
Control Panel
•GMAP – Ground map mode. GMAP label
displayed.
•Antenna Tilt +/- 15º
• Range indicators between +5º
& -5º are expanded
•FP – Flight Plan mode. Radar put in standby &
no radar data presented. A singular display of nav
data & a FLTPLN label displayed.
Clock
Avionic Switched
DC Bus
•TEST – Test pattern displayed with a TEST label.
•Antenna beam width 7.9º
Primary Flight
Display (PFD)
[Avionic Switched
DC Bus]
Digital Audio Panel (DAP)
Foot Warmer
Valve
Gasper vent
Switch altimeter ref.
between Inches and HPa.
Standard altimeter setting
button
Causes MFD to present PFD or
EICAS displays from on-side IC-600.
Switch on fwd side of
yoke disengages nose
wheel steering
DG – AHRS hdg channel
operates as free nonslaved gyro.
SLVD – AHRS slaved to
flux valve.
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.
Allows slewing of hdg
when AHRS not slaved to
mag hdg of flux valve.
Panel not present in
AH900 equipped a/c.
PSU O2 latches energized;
6 sec. timer
Remote
Start/Stop/Reset for
chronograph
Down – Off
Center – Hot Mic
Up - PTT
CLOSED – Disables PSU
O2 latches. Also resets O2
ON indicator & cabin signs
after system activation on
AUTO or MANUAL.
•Pitch Trim with 3
sec. timer
Touch Control Steering (TCS)
•Disengages AP
•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.
•Capt’s has priority
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.
ADC – selects cross-side ADC. ADC 1(2) on
PFD.
PFD comparison montiors
HDG
Δ > 6 for a/c roll < 6
or >12 for a/c roll > 6
ROL
Δ >6
PIT
Δ >5
ATT
if both ROL and PIT set
ALT
Δ 200 ft or more
IAS
Δ > 5 kts
LOC
Δ.> 1/2 dot (below 1200 ft.)
GS
Δ.> 2/3 do (below 1200 ft.)
ILS
if both LOC and GS set
25 February
2006, William
May
2008 William
de Grohde Groh
AHRS – selects cross-side AHRS. ATT 1(2) &
MAG 1(2) on PFD.
SG – selects cross-side symbol generator (IC600). ADC 1(2), ATT 1(2), MAG 1(2), & SG 1(2)
on PFD.
•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.
•Rotated CW to
EMERGENCY position
supplies 100% O2 under
positive pressure
•Pressed, tests regulator
demand mechanism
Vertical CDI Scaling per dot
For CN: GS = 0.35
For FMS: ENR = 750’
TERM = 0.35
APPR = 0.35
VNAV = 250’
AUTO – PSU O2 latches
energized & cabin signs on
when cabin altitude
> 14,000 ft.
MANUAL – activates PSU
O2 latches at any altitude.
•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
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
•Bank angle reduced from
27º to 14º in HDG mode .
•Auto selected climbing >
25,000 ft & canceled <
24,750 ft in HDG mode.
•Annunciated only in HDG
Select mode
Couples FD to nav
source selected on
flying pilot’s DCP.
VOR/LOC if NAV
selected and LNAV if
FMS selected
•Engages AP & YD
Same as NAV but
with higher gain.
Also enable GS
Mode.
•Hdg Hold (ROL) holds
present hdg when
selected
•Cycles between full
rose HSI & sector
format on PFD
•Pressed again
disengages AP but
keeps YD
•First press enters
Elapsed Timer Mode
•In sector format WX
radar can be displayed
•Start/Stop/Reset
Allows CA’s or FO’s FD
to control the AP
Cycles between on-side
VOR/LOC SRN source
(green) or cross-side
VOR/LOC SRN source
(yellow)
•Speed Hold Mode
•Flight Level Change
•Hdg Select (HDG)
follows hdg bug
•Vertical Speed Hold Mode
•Allows hdg selection
Cycles between on-side
FMS LRN source
(magenta) and crossside FMS LRN source
(yellow)
•Altitude Hold Mode
•Pressing synchronizes
hdg bug to current hdg
Displays FD bars
Master Warning Button
•Allows crs selection
•Engages YD
•Pressing synchronizes
selected course to VOR
bearing
Setting
Knobs
•Pressing again disengages
both AP & YD
Cycles between ground
speed and time-to-go.
Display Control
Panel (DCP)
OFF – Associated bearing
pointer sources disabled
NAV– Selects associated VOR
as bearing pointer source
Engine Indication & Crew Alerting System (EICAS)
ADF – Selects associated ADF
as bearing pointer source
Standby Attitude Indicator
•Pull to cage & rotate to
adjust miniature airplane
FMS – Selects associated FMS
as bearing pointer source
•Power warning flag
Power off
Caged
•Rotation allows setting
Radio Altimeter decision
height
Open motor winding
Loss of power
•Essential DC Bus 2
•On grnd, pressing activates
IC-600 first level IBIT test. If
held > 6 sec. activates IC600 second level IBIT test.
EICAS test commanded from
CA’s panel only.
Multi Function
Display (MFD)
Standby Airspeed Indicator
Standby Altimeter
•In flight, pressing activates
Radio Altimeter Test
Backup Ess Bus
Avionic Switched
DC Bus
Optional Integrated Standby
Instrument System (ISIS)
•Replaces the three
electromechanical standby
instruments with a single LCD
screen
•CAGE button resets attitude
only
•Inhibits EGPWS when approaching
airports not covered by EGPWS
database thus avoiding unwanted
terrain alerts.
•STD button sets standard
barometer setting
•The + or – keys adjust
brightness
•Rotary knob allows altimeter
setting
•Striped bar in button when pressed
•Cancels LANDING GEAR voice
msg. in case of Radio Altimeter loss
only when flaps < 22º
•TEST/RESET function
enabled by pressing ON,
waiting 1 sec. then
pressing ARM
•RESET function
deactivates ELT after
manual or auto activation
Some EICAS messages inhibited
Rotation allows setting
airspeed bug values
Rotation allows pilot to
scroll through EICAS
messages if display limit
of 15 exceeded.
•Striped bar in button when pressed
•Flight Level Change Mode
•Striped bar extinguishes if TLs
advanced or flaps set above 22º , or
gear down & locked
•Climb
•ON – Activates ELT
•ARM – Allows automatic
activation
100 +/- 10 ft
Indicates when
emergency/parking
brake is applied
Flashing ELT alert
light indicates ELT
transmitting
•Powered from Essential Bus 2
TEST displayed
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
“LANDING GEAR” voice msg activated when:
•Flaps < 22º, one TL < 45º (59º if OEI), and
Radio Altitude < 1200 ft. Can be canceled.
•Flaps set at 22º, one TL < 45º (59º if OEI), and
Radio Altitude < 1200 ft. Cannot be canceled.
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
•Flaps set at 45º. Cannot be canceled.
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
Takeoff: V1-15 to 400’ RA
Landing: 200’ RA to 3 sec. after W-on-W
25 February
2006, William
May
2008 William
de Grohde Groh
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
EMBRAER 145 CENTER PEDESTAL
•Disconnects CA’s
elevator control from
FO’s
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.
•Checks takeoff configuration warning by
simulating TLs advanced
•If ok, “TAKEOFF OK” voice message
•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.
•If fail, “TAKEOFF ___” voice message & NO
TAKEOFF CONFIG EICAS msg
FLAPS
SPOILERS
TRIM
•CA’s side has all AP
servos & stick pusher
BRAKES
•Cannot be reset in flight
•Disconnects CA’s
aileron control from FO’s
Illuminates when
disconnection
mechanism activated
•FO’s side has roll trim
actuator & artificial feel
unit
•Cannot be reset in flight
Illuminates when
disconnection
mechanism activated
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
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
cmd’d open when TLs
at soft detent (TLA 14º)
•Cmds outboard spoiler
panels to open when:
If OEI or one reverser
not deployed FADEC
will only cmd reverse
from good engine if TL
requesting reverse
and OEI TL set to
IDLE
TLA of both
engines < 50º
Flaps < 13º
•No intermediate
positions
Thrust Lever
Friction Knob
•Electrically controlled
thru DC Bus 1 & 2
•Electrically actuated &
controlled
•Hydraulically actuated
•DC Bus 1 & 2
•If one channel fails,
remaining motor can
drive flaps at half speed
•Pulling actuates
emergency brakes (no
anti-skid)
•3º asymmetrical limit
disables system for
duration of flight
•Pull & rotate to set
parking brake
•Always have toe
brakes applied when
setting or releasing to
prevent hydraulic fluid
transfer
Thrust Mode select buttons
(no ATTCS)
•All 4 brakes supplied
by Hyd Sys 2
proportional to handle
displacement with no
protections
•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.
25 February
2006, William
May
2008 William
de Grohde Groh
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 45º. SPS ICE SPEED msg
remains,or
on ground after pressing TEST button. SPS ICE
SPEED msg cleared.
CON thrust if one of the following:
•Cuts out SPS channel
1 or 2 in case of failure
•>300 ft AFL & gear not locked down, or
•Striped bar in button
when pressed
Limited to OEI only
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
• >1700 ft AFL
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
EMBRAER 145 AFT CENTER PEDESTAL
Control Display Unit (CDU) of
Universal UNS-1K Flight Management
System (FMS)
•Actuates yaw trim
•3 sec. timer in case of
trim knob failure
Pitch control wheel
inhibited if any Vertical
Mode selected in FD
•Cuts out (pressed) or
enables (released)
HSCU Main or Backup
Pitch Trim systems
•Striped bar in button
when pressed
Manually controls roll
attitude when AP
engaged
Actuates pitch trim
through the HSCU
backup channel
Actuates roll trim by
repositioning neutral
position of aileron
command
ARINC Communications And
Reporting System (ACARS)
Printer
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
Landing Gear Freefall Compartment
On floor between co-pilot’s seat and control pedestal
•ON inscription when
pressed
Electrical Override Switch
•Inhibited in MAN mode
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.
25 February
2006, William
May
2008 William
de Grohde Groh
•Auto mode (released) or
Manual mode (pressed)
•MAN inscription
illuminated when pressed
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.
Erases data only on the ground with
parking brake set. Only the
manufacturer can recover the “erased”
data.
•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.
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
•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.
•Connects (pressed) or disconnects
(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
•Tests integrity of CVR
•Green STATUS LED illuminates for
1 sec. if test is good
DC Bus 2, 2 hr recording,
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
5g switch
•Connects (pressed) or disconnects
(released) the 28 vDC, 400 Amp enginedriven 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.
•Connects (pressed) or disconnects
(released), 28 vDC 400 Amp, APU StarterGenerator when APU rotor speed > 95% +
7 sec.
•BATT 2 used to start APU
•Striped bar in button when released.
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 > 70C, 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.
•Powers TCAS II & GPWS
•Striped bar in button when released.
•Connects (pressed) or disconnects
•Connects (pressed) or disconnects
(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 shortcircuit or near zero system voltage.
25 February
2006, William
May
2008 William
de Grohde Groh
(released) the com/nav supplied by
Avionics Switched Buses.
•Allows prevention of undesirable voltage
transients during APU battery starts on
the ground.
•Striped bar in button when released.
•ON – Emergency lights ON using the 4 dedicated batteries; 15 min. duration; batteries not charging - EMER LT NOT ARMED
•OFF – 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.
EMBRAER 145 OVERHEAD CHANNEL B
FUEL 1 (2) LOW LEVEL
•Fuel remaining ranges from 463 to 584
lbs.
•Illuminates red upon fire detection
•Pulling will send close cmd to:
FUEL IMBALANCE
Hyd. Pump SOV
•Comes on at 800 lbs difference
Bleed Air SOV
•Goes off at 100 lbs difference
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.
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
•Selects which electric fuel pump will be
operating continuously for that engine
LOW 2 – opens cross-feed valve & shuts off
right selected electric fuel pump
•Remaining pumps of associated side are
kept in auto standby
•To cross-feed select tank with lower fuel
•If fuel pressure < 6.5 psi remaining two
pumps come on line & will cycle with
inoperative pump causing “clicking” in relay
box.
•Switch powered by Ess DC Bus 2
•Fuel Pump A on associated Essential Bus
•Fuel Pump B on cross-side Essential Bus
•Fuel tank temperature taken from left tank
only & displayed on MFD, FUEL page.
•Fuel Pump C on associated DC Bus
• FUEL TANK LO TEMP msg. indicates fuel
temp. inside left tank is < -40ºC
ON – Energizes selected pump
•E1 (2) FUEL LO TEMP msg. indicates engine
fuel temp. (leaving FCOC) is < 5ºC.
OFF – De-energizes selected pump
•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
Interphone Control Unit (ICU)
•Allows interphone com
between FA and pilots.
•Generates a cabin chime to call FA
•Generates cabin chime
•On FA’s Call Panels:
PILOT
•Allows interphone com between pilots and
FA in case of normal mode failure
•Striped bar when button
when pressed
•Illuminated CABIN and CAB EMER buttons
on ICU, and PILOT and EMER PILOT
annunciators on Attendant’s Call Panel
•Striped bar in button when pressed
Same as CABIN button
except on F/A’s Call Panels:
EMER
PILOT
•Turns on or off the associated lights
DFDR begins recording when RED
BCN switch in ON or A/C is airborne
25 February
2006, William
May
2008 William
de Grohde Groh
.
EMBRAER 145 OVERHEAD CHANNEL C
Permits testing the fire detection system
•Class C baggage compartment
On grnd, if pressed & held > 10 sec. APU
auto shut down in the same manner as if
the FUEL SHUTOFF button was pressed.
•Two cargo extinguisher bottles located in
rear Electrical Compartment
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.
•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
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
•Two smoke detectors – Maintenance must
reset
•Sight glass in lavatory
•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
•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)
•Striped bar in button when pressed
APU Normal Shutdown
•Sends stop request to FADEC and closes the
APU Main Fuel Solenoid Valve (at the APU).
APU start cycle:
3% (0% airborne): ignition energized & Main
Fuel Solenoid Valve opens
50%: Starter de-energized
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.
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%.
OFF – De-energizes ignition system
AUTO – Active FADECs control ignition
system automatically
RESET – Resets FADEC & clears faults
ALTN – Alternates FADEC in control
•Inoperative if held > 3 sec.
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.
Enabled on grnd only with TLA < 50º
 First flt of day
1st press – enables T/O Mode setting
Cold eng. starts SAT or oil < 5ºC
2nd
press – REF TO TEMP
External air or Crossbleed start
3rd press – REF A-ICE
Contam.runway TO AND < 10ºC.
4th press – stores values. Data accepted if
REF TO TEMP within +/-10ºC & both
engines running
Moderate or > turb. or heavy precip.
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
Turns on/off wing landing lights
•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)
25 February
2006, William
May
2008 William
de Grohde Groh
EMBRAER 145 OVERHEAD CHANNEL D
•Illuminates red upon fire detection
Automatic Rudder Shutoff Through Speed Switch
•Pulling will send close cmd to:
•Rudder limiter for high speed
Hyd. Pump SOV
•Rudder Sys 1 auto shutoff > 135 kts to reduce
rudder authority at high speed
Bleed Air SOV
Engine Intake Lip Anti-ice SOV
•If Sys 2 fails Sys 1 comes back on line
automatically with EICAS message
Fuel SOV.
•RUDDER OVERBOOST if neither Sys shuts off
> 135 kts
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.
Rudder Hardover Protection (for low speed)
•Both Sys 1 & 2 auto shutoff
Force on any pedal > 130 lbs, and
Rudder deflected > 5º 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 5º
•Inhibited with OEI operation
•Enables (pressed) or disables
(released) associated hydraulic
system pressure to both aileron
actuators.
•Enables (pressed) or disables
(released) associated rudder hydraulic
actuator.
•Striped bar in button when released
•Striped bar in button when released
•Hyd. Pump driven by engine accessory
gear box
Priority Valve
•Provides 3000 + 100 psi @ 9.2 gal/min
•Only on Hyd Sys 1
•E1 (2) HYD PUMP FAIL msg < 1600
psi or N2 < 56.4%
•Priority valve closes during ldg
gear operation with only electric
hyd. pump supplying system, to
isolate ldg. gear giving priority to
the flight controls.
•HYD 1 (2) LO QTY msg if reservoir < 1
liter
•Reservoir capacity 6 liters
24 hr parking brake or 6 full
emerg. brake applications
Accumulator
Emerg. Brake
Accumulator
An accumulator is basically a
“hydraulic battery” storing
hydraulic energy & providing
surge protection.
•Closes (pressed) or opens (released)
engine-driven Hyd. Pump SOV
•Hyd. Pump continues to run if engine
running
•Striped bar in button when released
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
Control logo lights on
underside of
horizontal stabilizer
25 February
2006, William
May
2008 William
de Grohde Groh
Control cockpit
dome lights at a
fixed intensity
•Turns signs on or off with a
chime
•Both signs are automatically
activated when pax O2
dispensing units open
EMBRAER 145 OVERHEAD CHANNEL E
•Off (released) or selects auto mode
(pressed) of wing and/or horizontal stabilizer
A/I valves. L pneumatic supplies horizontal.
•Off (released) or permits (pressed)
automatic activation of engine lip anti-icing
•OPEN inscriptions indicates engine lip antiice valve open
•OPEN inscription means valves open with
system cmd’d open or at least one valve
open with system not cmd’d open.
•Striped bar in button when released
•Source is a valve upstream of HSV with no
temperature control (i.e. EBVs can be
closed & still operate)
•Striped bar in button when released
•Can be open on the grnd without limitation
•On (pressed) or off (released)
•Off (released) or auto mode (pressed)
•Striped bar in button when released
•Striped bar in button when released
•Defog mode if no ice detected - maintains
windshield at 26 C. If ice cond. anti-ice
mode holds windshield at 43 C
•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%
•3 sensors, 1 temp control, 1 overheat
protection, 1 spare
•Separate logic ensures Pitot/Static 3 & Press.
Sys. Static Port 2 heated in any flight condition
•Should be off when OAT > 10ºC on grnd
•TAT 1 & 2 heat when TLs > 65º TLA (~78.5 to
82.5% N1) and assoc. engine A/I system on,
OR anytime inflight.
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.
•EICAS msg inhibited during takeoff & landing.
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)
Permits testing wing, horizontal stabilizer,
and engine anti-ice valves by simulating an
ice condition on ice detectors 1 & 2.
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- right pack automatically
controlled between 18ºC and 29ºC by
Digital Temperature Controller
•Pull for manual operation
•ATTD – Control transferred to FA Panel
where green ON light illuminates.
•Pressed- left pack automatically controlled
between 18ºC and 29ºC by Digital
Temperature Controller.
•On (pressed) or off (released) AIRBORNE
ONLY
•Pull for manual operation
•Gasper ON with DC Bus 2 energized on grnd
regardless of button position
•On (pressed) or off (released)
•Striped bar in button when released
•Controls both recirc fans. On grnd
during hot soak days must be OFF;
during cold soak days must be ON
•Supplies gaspers, and ventilation for the O 2
cyl. cmpt., relay boxes, and rear elect. cmpt.
•Striped bar in button when released
CLOSED – Closes CBV
OPEN – Opens CBV (CROSS BLD OPEN)
AUTO – Automatic operation of CBV
•Opens (pressed) or closes (released) the
Pack Pressure Regulating and SOV (PRSOV)
•Electrically controlled, pneumatically
actuated
•Striped bar in button when released
•On grnd, with main door open & pack <
227ºC PRSOV operates in high mode, other
times in low mode
•EBV (PRSOV) open (pressed) only when
bleed air demanded or closed (released).
•PACK 1 closes with A/I on below 24,600 ft
provided PACK 2 operating
•Engine inlet lip A/I taken upstream of HSV
•LEAK inscription indicates duct leakage.
•HSV (14th stage) open during low thrust,
crossbleed starts, and A/I operations
•Max thrust (takeoffs & go-arounds) with EBVs
open, Pack Valves automatically close by
FADEC when:
•9th stage air joins 14th stage, both with
BACVs, then thru precooler upstream of EBV
 OEI up to 9700’ MSL & TAT >19ºC at
S.L. decreasing to -5ºC at 9700’ MSL
•EBV closed by Fire Handle or automatically
with intense hot air leak (BLD VLV CLOSED)
AEO up to 1700’ AGL & TAT >19ºC
decreasing to -5ºC at 9700’ MSL
•Used for engine start, ECS, pressurization,
& ice protection
•Must reset Pack Valves after auto shutdown
•If both Pack Valves closed in flight the ram
air valves open & recirculation fans auto
shutdown.
•Opens (pressed) or closes (released) ABV.
Striped bar in button when pressed
•On the ground the ram air valves are always
closed, regardless of Pack Valve position.
LOW – 80 strokes/min
HI – 140 strokes/min
“BLEED TEMP” on ECS page of MFD is
taken downstream of precooler.
•APU bleed air not sufficient for A/I
TIMER – Intermittent operation, 2 strokes at high
speed with 8 sec. delay
•Auto closes if LH EBV or RH EBV with CBV
are open to prevent reverse flow. BACV
downstream of ABV for same purpose.
Dry windshield protection parks blades until knob
cycled to OFF to reset.
•Electrically controlled & pneumatically
actuated
Maximum speed for operation - 160 KIAS
25 February
2006, William
May
2008 William
de Grohde Groh
•OPEN inscription indicates ABV in open
position
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
Radio Management Unit (RMU)
•Pressing allows Data
Acquisition Unit (DAU) Channel
B to supply both IC-600
•Striped bar in button when
pressed
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.
25 February
2006, William
May
2008 William
de Grohde Groh
NORM – RMU tuning available
EMERG – tuning through RMU
inhibited
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.
Tuning Backup Control Head (TBCH)
Allows alternative means of tuning Com
2 and Nav 2
NAV (VOR/ILS) – Hold for 20 sec.