Embraer 190 Lights And Switches

Front 1

Dome Light Switch

Back 1

Batteries must be ON/AUTO to have dome lights on

Front 2

CVR Erase

Back 2

Must be on the ground with parking brake set

Front 3

DVDR Test

Back 3

Self test of DVDR 1 and DVDR 2. Failure is indicated by CVR AFT(FWD) Fail

Front 4

IDG 1 and IDG 2 Selector Knob

Back 4

Auto: Allows IDG Contactor to close, connecting the IDG to the respective AC bus automatically, according to system logic

OFF: Opens the IDG contactor isolating the IDG from the respective bus

Front 5

Normal AC Bus Source Priority

Back 5

Respective IDG, then AC Bus Tie

Front 6

When does IDG LED Illuminate?

Back 6

IDG 1(2) Oil caution

Front 7

AC Bus Ties Selector Knob

Back 7

1 Open: Opens the BTC 1, segregating AC BUS 1 from the AC BUS TIE

AUTO: Allows automatic operation of the BTC's according to system logic

2 Open: Opens the BTC 2, segregating AC BUS 2 from the AC BUS TIE

Front 8

AC BUS TIE Priority

Back 8

APU

GPU

IDG

Front 9

GPU Button

Back 9

Push In: Connects the AC GPU to the AC BUS TIE, according to source priority

Push Out: Isolates the AC GPU from the AC BUS Tie

Front 10

GPU Avail Light

Back 10

Illuminates with the GPU button pushed in or out when the AC GPU is connected to the aircraft, but not powering the AC BUS TIE.

Front 11

GPU IN USE Light

Back 11

Will only illuminate when the button is pushed in, and the AC GPU is powering the AC BUS TIE

Front 12

APU GEN Button

Back 12

Push in: allows the APU generator to connect to the AC BUS TIE, automatically according to source priority

Push Out: Opens the APU generator contactor and isolates the APU generator from the AC BUS TIE. The APU generator is tripped off line and de-excited

Front 13

TRU ESS Toggle Switch

Back 13

AUTO: allows for automatic connection of the TRU ESS to the ESS BUS 3

OFF: Isolates the TRU ESS from the ESS BUS 3

Front 14

TRU 1 and TRU 2 Toggle Switch

Back 14

Auto: Allows automatic connection of the TRU to the respective DC BUS

OFF: Isolates the TRU from the respective DC BUS

Front 15

Batt 1 Selector Knob

Back 15

ON: Battery is connected to the DC ESS BUS 1

OFF: Battery supplies to HOT BATT BUS 1 only

Front 16

DC BUS TIES Toggle Switch

Back 16

AUTO: Allows automatic operation of the DC TIE contactors (1DCTC/2ETC's) according to system logic

OFF: Opens all DC TIE contactors

Front 17

BATT 2 Selector Knob

Back 17

AUTO: Connects BATT 2 to either the DC ESS BUS 2 or the APU START BUS automatically, according to system logic

OFF: THe battery supplies power to HOT BATT BUS 2 only

Front 18

Fuel XFEED Selector Knob

Back 18

Low 1: Opens the cross feed valve, and activates AC Pump 2 to supply fuel to both engines from the right wing tank

Front 19

DC PUMP

Back 19

OFF: Deactivates the DC Fuel Pump
Auto: Allows automatic operation of the DC Pump in accordance with system logic

ON: Activates the DC fuel pump

Note: The DC PUMP will activate for APU start if AC power is not available. The DC Pump is not a backup for the AC Pump

Front 20

AC PUMP 1 and AC Pump 2

Back 20

OFF: Deactivates the associated AC PUMP
AUTO: Allos automatic operation of the associated AC PUMP in accordance with system logic
ON: Activates the Associated AC PUMP
Note: The The AC PUMP will activate automatically when fuel pressure is demanded and ejector output is insufficient (engine start or ejector pump failure), and for XFEED operations. Additionally, when AC power is available on the ground AC PUMP 2 will run for APU Start, and to feed the APU.

Front 21

EMER LT Selector Knob

Back 21

EMER LT Selector Knob
OFF: Disables automatic operation of the emergency lights. The lights can still be turned on from the FWD or AFT ATTENDANT panel.
ARMED: Automatically illuminates all emergency lights if
DC BUS 1 loses power or if the airplane electrical power is
turned off.
ON: Turns on all emergency lights regardless of the position of the EMERGENCY LIGHT switch on the FWD and AFT ATTENDANT panels.

Front 22

#1 and #2 Engine Fire EXTG Handle

Back 22

PULL: Closes the associated engine bleed air, fuel,
and hydraulic shutoff valves. The under speed logic will
eventually open the generator line contactor as the engine
decelerates.
ROTATE (left (A) or right (B)): Discharges the associated
fire extinguisher bottle into the associated engine

Front 23

APU Swiitch (Guarded)

Back 23

Momentary action pushbutton.
Closes the APU fuel shutoff valve and discharges the APU
fire extinguisher bottle. The light will illuminate when an APU fire has been detected and the APU EMER STOP button has been pushed in, or 60 seconds after an APU fire has been detected and no pilot action has occurred. If no fire is detected, one push will arm and discharge the fire bottle
NOTE: The aircraft must not be left unattended with the APU
running because the APU fire bottle will not automatically
discharge in the event of a fire

Front 24

Cargo Smoke FWD and AFT buttons in Flight

Back 24

smoke detected (EICAS MSG + Light Illuminates )
IN FLIGHT: a single button push will discharge the HIGH
rate bottle. 60 seconds later the LOW rate bottle will
discharge automattically.

smoke not detected (No EICAS MSG or Light)
IN FLIGHT: a single button push will arm the HIGH
rate bottle (light comes on). A second button push will
discharge the HIGH rate bottle. 60 seconds later the
LOW rate bottle will discharge.

Front 25

Cargo Smoke FWD and AFT buttons on Ground

Back 25

(EICAS MSG + Light Illuminates ) smoke not detected
ON GROUND: a single button push will discharge the
HIGH rate bottle. Automatic discharge of the LOW rate
bottle is inhibited on the ground. However, a second
button push will discharge the LOW rate bottle.
(No EICAS MSG or Light)
ON GROUND: a single button push will arm the HIGH rate
bottle (light comes on). A second push will discharge
the HIGH rate bottle. A third button push will discharge
the LOW rate bottle.

Front 26

Fire Detection System TEST Button

Back 26

Momentary action button. Tests the engine and APU
fire detection systems, and the forward and aft cargo
compartment smoke detection systems. Prior to performing a FIRE TEST confirm that there are no FIRE DET FAIL, FIREX FAIL, FIREX ARM, or BTL DISCH messages on the EICAS

Front 27

APU MASTER Knob

Back 27

OFF: Normal position when the APU is not running.
ON: Normal position when the APU is running. APU FADEC
faults that command automatic shutdown of the APU will
command shutdown in 10 seconds after the fault is detected.
START: (Momentary action) Initiates the APU start cycle.
NOTE 1: Moving this knob from ON to OFF starts the APU
shutdown process. The process involves a one minute cool down. During the cool down APU pneumatics are removed as soon as the MASTER rotary knob is positioned to OFF. If the APU generator is the only source of AC power during the cool down, then APU electrical power will still be available during the one minute cool down period. If there is any other source of AC power on the aircraft when the MASTER rotary knob is moved to OFF, then APU electrical power is removed right away.
NOTE 2: During any portion of the one minute cool down,
1 2
APU CONTROL Panel
the MASTER rotary knob can be moved from OFF back to
ON and the APU will continue running

Front 28

EMER STOP Button (Guarded)

Back 28

PUSH IN: Closes the APU fuel shutoff valve, shutting down
the APU without a one minute cool down. Selection of this
button will illuminate a white stripe in the lower half of the
APU EMER STOP button.
PUSH OUT: Normal position, with the fuel shut off valve
open.
NOTE: In case of fire, the upper half of the button illuminates red. When pushed in, a white striped bar illuminates on the lower half of the button.

Front 29

PTU Switch

Back 29

OFF: Turns the PTU off.
AUTO: Assists with landing gear extension or retraction
when there is low pressure in Hydraulic System 2 (Engine 2 failure or loss of EDP 2).
ON: The PTU operates continuously

Front 30

SYS 1 and SYS 2 ENG PUMP SHUTOFF Buttons
(Guarded)

Back 30

Momentary action pushbuttons.
PUSH IN: Closes the hydraulic shutoff valve (SOV), isolating the respective EDP from the associated hydraulic system.

PUSH OUT: Normal position. Hydraulic SOV open.

Front 31

SYS 1 and SYS 2 ELEC PUMP Selector Knobs

Back 31

OFF: Turns the associated electrical pump off.
AUTO: On Ground: SYS 1 and SYS 2 will run automatically for takeoff (flaps are not set at zero; and the thrust levers are advanced for takeoff, or the ground speed is greater than 50 kts). Additionally, the SYS 2 ELEC PUMP will run automatically for single engine taxi when ENG 1 has been started and the EMERG/PRKG BRAKE Handle has been released.
In Flight: SYS 1 and SYS 2 will operate automatically when
low pressure is detected, or for landing (flaps are not at
zero).
ON: Operates the electrical pump continuously

Front 32

SYS 3 ELEC PUMP A Selector Knob

Back 32

OFF: Turns the electrical pump off.

ON: Operates the electrical pump continuously

Front 33

SYS 3 ELEC PUMP B Selector Knob

Back 33

OFF: Turns the electrical pump off.

AUTO: In flight only, the pump will turn on when low pressure
is detected.
ON: Operates SYS 3 B pump continuously.

Front 34

Pressurization MODE Selector Knob

Back 34

MAN: Allows manual control of the outflow valve (OFV).
AUTO: Allows automatic operation of the pressurization
system.
LFE CTRL: Allows manual input of landing field elevation.
This function is used when the FMS is inoperative, or
when landing at an airport not in the FMS database. Other
automatic functions of the pressurization system remain
operative

Front 35

DUMP Button (Guarded):

Back 35

When pushed in a white striped bar will illuminate in the
button. With the pressurization mode in MAN or AUTO,
pushing this button in will turn off both sets of air conditioning packs and recirculation fans allowing the aircraft to depressurize . Additionally, in AUTO only, the outflow valve will modulate to raise the cabin to 12400’ at 2000’ fpm. Once the cabin has been dumped to 12400’ natural leak will raise the cabin higher. If a cabin dump has been commenced, it can be cancelled by reselecting the button to its normal (out) position.
NOTE: Selecting the DUMP button in while in MAN mode will still command the PACK’s and RECIRC FAN’s to shutdown

Front 36

CAB ALT Selector Knob

Back 36

Rotary knob is only active when the pressurization MODE
knob is selected to MAN.
DOWN: Manually closes the OFV.
STOP (Spring Loaded): Normal operation position.
UP: Manually opens the OFV

Front 37

LFE Knob

Back 37

Manual input of the LFE is only possible when the
pressurization MODE knob is selected to LFE.
DOWN: Decreases the LFE.
STOP (Spring Loaded): Normal operation position.
UP: Increases the LFE

Front 38

WINDSHIELD HEATING BUTTON 1 and 2

Back 38

PUSH IN: Allows automatic operation of the associated
windshield heating system.
PUSH OUT: Deactivates the associated windshield heating
system.
NOTE: On the ground the windshields will be heated for
approximately two minutes during the PBIT. After the PBIT is complete the windshield heaters will operate normally only with two sources of AC power (excluding GPU).
NOTE: In flight with only one source of AC power, power
to the F/O’s windshield is shed. In the event the Captain’s
windshield is inoperative, power will be supplied to the F/O’s windshield.

Front 39

WING ICE PROTECTION Button

Back 39

Ground: Wing anti ice is selected ON from the MCDU, TRS
INDEX, TO DATA SET MENU, REF A/I LSK.
In-flight: Operation is automatic through the AMS.

PUSH OUT: Deactivates the wing anti-ice system.

Front 40

ENGINE ICE PROTECTION Button

Back 40

PUSH IN: Allows automatic operation of the associated
engine anti-ice system.
Ground: Engine anti-ice is selected ON from the MCDU,
TRS INDEX, TO DATA SET MENU, REF A/I LSK.
In-Flight: Operation is automatic through the AMS.
PUSH OUT: Deactivates the associated engine anti-ice
system.

Front 41

ICE PROTECTION MODE Selector Knob

Back 41

AUTO: Allows automatic operation of the wing and engine
anti-ice systems.
ON: Overrides the system logic inflight, activating the anti-ice system regardless of icing condition.
Note:After landing, if the ICE PROTECTION MODE Selector Knob is selected ON, only the Engine Anti-Ice System is operative.

Front 42

Pneumatic source priority?

Back 42

Pneumatic bleed source priority for the packs and wing
A/I is respective side bleed, opposite side bleed (using
xbleed valve), and then APU bleed. When the airplane is
on the ground and engine and APU bleed are available
simultaneously, the AMS gives priority to APU to supply
bleed requirements for engine start.

Front 43

RECIRC Button

Back 43

PUSH IN: Allows for automatic operation of the RECIRC fans through the AMS.
PUSH OUT: Turns off both RECIRC fans.
NOTE: The RECIRC fans will automatically be commanded off when the DUMP Button is selected IN, smoke is detected in the recirculation bay, or when its associated pack is OFF

Front 44

PACK 1 and PACK 2 Buttons

Back 44

position opens the associated pack valve, according to system logic.
PUSH OUT: Manually closes the associated pack valve.
NOTE: PACK 1 and PACK 2 will be automatically commanded
OFF when the DUMP button is selected IN, the thrust levers are set to MAX, or during takeoff with REF ECS OFF and APU BLEED unavailable

Front 45

XBLEED Button

Back 45

PUSH IN: Allows the AMS to control automatic operation of the cross bleed valve.

PUSH OUT: Manually closes the cross bleed valve

Front 46

BLEED 1 and BLEED 2 Buttons

Back 46

PUSH IN: Allows the AMS to automatically configure the
position of the associated engine bleed valve.
PUSH OUT: Manually closes the associated engine bleed
valve.
NOTE: An engine bleed leak will cause the illumination of an amber striped bar in the upper half of the associated engine bleed button

Front 47

APU BLEED Button

Back 47

PUSH IN: Allows the AMS to automatically configure the
position of the APU bleed valve.
PUSH OUT: Manually closes the APU bleed valve.
NOTE: An APU bleed leak will cause the illumination of an
amber striped bar in the upper half of the APU BLEED button

Front 48

MASKS DEPLOY Knob

Back 48

OFF: Disables automatic deployment of passenger oxygen
masks.
AUTO: Enables automatic deployment of passenger oxygen masks when cabin pressure altitude is above 14000 ft.
OVRD: Deploys the passenger oxygen masks regardless of cabin altitude.
NOTE: The NO SMKG and FSTN BELTS will automatically
illuminate when the oxygen masks are commanded to
deploy.

Front 49

MASKS DEPLOYED Indicator

Back 49

An ON light illuminates, indicating that the passenger and
flight attendant oxygen masks have been commanded to
deploy

Front 50

#1 and #2 WINDSHIELD WIPER Controls

Back 50

TIMER: Provides eight-second intermittent operation.
OFF: Stops windshield wipers in the stowed position.
LOW: Windshield wipers operate at low speed.
HI: Windshield wipers operate at high speed.
NOTE: If both the windshield wiper knobs are selected
to LOW/HI they will sync to the Captains (#1) controller.
Windshield wipers will not operate on a dry windshield

Front 51

ADS Button

Back 51

Manually reverts the ADS source
Reversion to ADS 3 is automatic

Front 52

IRS Button

Back 52

Momentary action pushbutton:
Reverts the IRS source.
When IRS source reversion is selected, a white striped bar
illuminates in the button.
NOTE 1: IRS source flag is displayed on the PFD.
NOTE 2: IRS reversion must be performed manually

Front 53

AUTOBRAKE Selector Knob

Back 53

RTO: Selects maximum braking with anti-skid protection.
OFF: Autobrake is deactivated.
LO: Selects the low deceleration rate.
MED: Selects the medium deceleration rate
HI: Selects the high deceleration rate

Front 54

Autobrake Wheel Speed

Back 54

60 knots

Front 55

GND PROX TERR INHIB Pushbutton

Back 55

When pressed, inhibits EGPWS and thus avoids unwanted
terrain alerts in airports not covered by EGPWS database

Front 56

EMERG/PRKGBRAKE Light

Back 56

The word “ON” illuminates when the EMERG/PRKGBRAKE
is actuated. Illumination of the light indicates that sufficient
hydraulic pressure is available to maintain brake pressure.

Front 57

EICAS Declutter

Back 57

The following items are de-cluttered from EICAS
•Oil pressure.
•Oil temperature.
•Engine vibration.
•Slat position.
•Flap position.
•Speed brake position.
•Landing gear position (if
AUTOBRAKES are OFF)
•Pitch trim green band.
In normal conditions, de-clutter will be disabled when one
of the above parameters is no longer in a normal indicating
range, not stowed, or not up and locked. Additionally, arming
the AUTOBRAKE for landing will disable the de-clutter
function of the EICAS

Front 58

GND PROX G/S INHIB Button

Back 58

Momentary pushbutton annunciator used to manually cancel
glideslope alerts.
Illuminates when pressed any time below 2000 ft RADAR
altitude and will automatically reset (light off) by climbing
above 2000 ft RADAR altitude or descending below 30 ft.
RADAR altitude

Front 59

LG WRN INHIB Button

Back 59

Pressing the button will inhibit the landing gear warning in
the event of a dual radio altimeter failure. When pressed a
white striped bar will illuminate inside the button. The light
will extinguish allowing a new warning when the thrust levers
are advanced.
NOTE: If FLAP 5 or FULL is selected with the gear up the
warning cannot be cancelled

Front 60

DUMP Button

Back 60

Pressing the DUMP button will command potable water
drainage. When pushed a white striped bar will illuminate
inside the button. Pushing the button a second time will
end the dumping process, and the white striped bar will
extinguish. In order to drain the potable water tank the
aircraft must be airborne with the landing gear up and the
drain masts heated. Complete drainage of the tank can only
be confirmed on the Aft Attendant Control Panel

Front 61

HEATER Button

Back 61

PUSH IN: Activates the ADS probes heater. A white striped
bar illuminates.
PUSH OUT: The ADS probes heater works in AUTO mode

Front 62

START/STOP Selector Knob

Back 62

STOP: Commands the FADEC to shut down the engine,
provided the associated thrust lever is in the IDLE position.
RUN: Normal position for engine operation.
START: (Momentary action): Initiates the engine start
sequence

Front 63

IGNITION Selector Knob

Back 63

OFF: Deactivates the ignition system on the ground. When
dry motoring on the ground there is no fuel flow. The FADEC
disregards the OFF position in flight.
AUTO: FADEC automatically controls the ignition system,
depending on engine requirements.
OVRD: Directs FADEC to continuously activate both igniters

Front 64

FLIGHT CONTROLS MODE Buttons (GUARDED)

Back 64

PUSH IN: Selects DIRECT MODE for the associated flight
control. A white bar will illuminate in the push button.
NOTE: In DIRECT Mode high level functions are lost.
PUSH OUT: Returns the associated flight control to
NORMAL MODE

Front 65

SHAKER CUTOUT Button

Back 65

PUSH IN: Cuts out the associated yoke shaker channel.
PUSH OUT: Allows normal operation of the stick shaker

Front 66

T/O CONFIG Button

Back 66

Checks the takeoff configuration. The takeoff configuration
checks for EMERG/PRKG BRAKE OFF, takeoff flaps set,
EICAS flap position matches MCDU TAKEOFF Page 2/3 flap
setting, sploilers retracted and pitch trim in the green band

Front 67

EICAS FULL Button

Back 67

PUSH IN: Full EICAS information is presented and auto
declutter is inhibited. A white striped bar illuminates in the
button.
PUSH OUT: Enables the automatic EICAS de-clutter logic.
NOTE: Automatic de-clutter of the EICAS occurs 30 seconds
after gear and flap/slat retraction if all parameters are
displaying normal indications. The following items are decluttered
from the EICAS:
•Oil pressure.
•Oil temperature.
•Engine vibration.
•Slat position.
•Flap position.
•Speed brake position.
•Landing gear position (if
AUTOBRAKES are OFF)
•Pitch trim green band

Front 68

Speedbrake Lever

Back 68

In flight, symmetrically deploys the multi-function spoilers
in proportion to the speedbrake lever position. The
speedbrakes will automatically retract when the thrust levers
are advanced, greater than FLAP 1 is selected, or the speed
drops below 180 KIAS.
NOTE: The speedbrake lever does not move for
autoretraction, or for ground spoiler deployment.
NOTE: The speedbrake lever is inhibited on the ground

Front 69

Thrust Levers

Back 69

MAX: Provides the maximum thrust available.
TOGA: Selects takeoff, go around, and maximum continuous
thrust ratings.
IDLE: Selects idle thrust settings.
MIN REV: Provides minimum reverse thrust.
MAX REV: provides maximum reverse thrust. The thrust
lever must be pulled against a spring to achieve the MAX
REV position. If the thrust lever is released it goes back to
MIN REV position.
NOTE: Positioning the thrust lever between the thrust control
quadrant detents selects intermediate thrust settings.

Front 70

Flap Override Switch (GUARDED)

Back 70

Inhibits triggering of flap alerts in case of landings where flap
configuration is other than 5 or FULL.

Front 71

MIC/MASK Switch

Back 71

AUTO (PUSHED IN): Automatically turns on the mask
microphone when the oxygen mask is removed from its
cabinet, or is tested.
MASK (PUSHED OUT): Turns on the oxygen mask
microphone. This function is used if the AUTO mode does
not work.
Oxygen mask stowage box doors must be closed and the
TEST/RESET button selected in order to enable the hand
mic or headset boom microphone after using the oxygen
mask

Front 72

BKUP VOL Switch

Back 72

NORM (PUSH IN): Normal operation mode.
BKUP (PUSH OUT): Selected when the ACP fails or both
digital audio busses fail. The CAPT will be connected to
COMM1 only and the FO will be connected to COMM2 only

Front 73

SELCAL Button

Back 73

When a SELCAL is received the button will flash green, a
single chime will be heard, an EICAS message will post,
SELCAL will post in the ACP LCD, and the MIC and AUD
button of the called channel will flash green. Holding down
the SELCAL pushbutton will display the SELCAL code
that has been programmed for the aircraft. The button will
illuminate steady green when active for transmission.

Front 74

TRIM Panel

Back 74

Pitch trim priority is backup trim, Captain trim, First Officer
trim, and the autopilot trim. To prevent trim runaway
situations all trim actuation is limited to three seconds of
movement. The switches on both pilot yokes, the PITCH
BACKUP SW trim switch, and the ROLL trim switch are
split rocker type switches. If one half of a switch is actuated
for more than 5 seconds that particular switch will be
deactivated

Front 75

SYS 1 CUTOUT Switch (GUARDED)

Back 75

PUSH IN: Disables pitch trim channel 1.
PUSH OUT: Enables pitch trim channel 1

Front 76

LOCK Pushbutton (GUARDED)

Back 76

Locks and unlocks the door. A white bar in the switch
illuminates when unlock is selected (push in). Deactivates
the inhibition control. Resets the buzzer alarm and EMERG
CALL command. Resets the green LED on the flight
attendant access panel

Front 77

INHIB Pushbutton (MOMENTARY ACTION)

Back 77

Pushing this button will inhibit cockpit entry 500 seconds if
emergency access is requested. When pushed, an amber
bar will illuminate in the button. If emergency access is
requested and INHIB is not selected within 30 seconds, the
door will unlock. Note: When the 500 second timer concludes, the cockpit
door will remain locked

Front 78

UNLOCKED Indicator

Back 78

Illuminates ON when the door is unlocked. When access is
requested an intermittent chime will sound in the cockpit and
the ON light will flash on and off

Front 79

ELEVATOR DISCONNECT Handle

Back 79

PULL: Disconnects the elevator control system. Each pilot
will control their on-side elevator. The system cannot be
reset in flight. Disconnection can be confirmed by a cyan
ELEVATOR DISC EICAS message

Front 80

AILERON DISCONNECT Handle

Back 80

PULL: Disconnects the aileron control system
CAPTAIN: Controls his/her onside aileron, and one set of
MFS panels on each wing. The Captain maintains artificial
feel
First Officer: Controlls his/her onside aileron, and one
set of MFS panels on each wing. There is no artificial feel
available on the first officer side
The system cannot be reset in flight. Disconnection can be
confirmed by a cyan AILERON DISC EICAS message.

Front 81

Alternate Gear Extension Lever (Two Position)

Back 81

When pulled releases all hydraulic fluid from the landing gear
lines and releases all landing gear uplocks

Front 82

Electrical Override Switch

Back 82

NORMAL: The landing gear lever performs landing gear
extension and retraction (FWD position).
GEAR DOWN: Bypasses the landing gear lever and extends
Alternate Gear Extention Compartment the landing gear (AFT position).

Front 83

TO on FMA during taxi/ takeoff

Back 83

Take Off is the active vertical mode. Pitch commands are given to an initial target attitude for rotation, followed (after liftoff) by
commands to maintain airspeed between V2 and V2+10 (as programmed in FMS). NOTE: TO mode provides FD guidance only,
and cannot be flown by the AP; engagement of AP in TO mode will cause vertical mode to revert to FPA.

Front 84

HOLD on FMA

Back 84

Takeoff Thrust Hold Control mode is active. HOLD mode activates when IAS is greater than 60 kts and deactivates at 400’
AGL. The AT servos are de-energized.

Front 85

TRACK on FMA

Back 85

Track mode is the active lateral mode. Bank commands are given to maintain the ground track that the airplane was on at the
moment of engagement. Engages automatically at 100 kts on takeoff when TO is the active vertical mode