System Buttons

Question 1

Answer 1

In auto mode ADSP/TAT heat system controls/monitors probes as soon as airplane powered. System can be overridden manually. PROBES 1-4 Knob commands left TAT, ADSP 1, ADSP 4. PROBES 2-3 Knob
commands right TAT, ADSP 2, ADSP 3.
ADSP/TAT logic activates probe heating
whenever in AUTO and following conditions:
ADSP:– Engine running and < 65 kt – Intermittent heating;
– Engine running > 65 kt – Full heating.
TAT probes:– engine running > 50 kt – Full
heating

Question 2

Answer 2

APU ON/OFF BUTTON–
PUSH OUT (OFF): shuts down immediately, removes power to FADEC after 5 minutes, closes APU fuel SOV;
PUSH IN (ON): activates FADEC power, starts FADEC power-up sequence. Power-up sequence includes APU Built-In Test (BIT) and APU fuel Shutoff Valve (SOV) test. After test completed, the APU fuel SOV commanded open.
NOTE: After APU shutdown, APU will take 40 seconds to completely stop to ensure it will not be providing remaining electric current to electrical system.
APU START BUTTON–
PUSH OUT: normal operation. The APU is commanded to off
PUSH IN: commands the APU start.
Green striped bar flashes during FADEC BIT at power up. Will become steady to indicate APU ready to start; Amber striped bar indicates APU start inhibited due to unsuccessful FADEC BIT, APU fuel SOV declared failed by FADEC, or when APU protective shutdown occurred.

Question 3

Answer 3

APU fire extinguishing system consists of one fire extinguishing bottle (bottle B), installed in aft fuselage. Bottle B shared among engines and APU.
Fire Protection APU Button, will be armed only if APU SHUTOFF Button, on APU CONTROL Panel is pressed. The bottle is one-shot type. By pressing Fire Protection APU Button, extinguishing agent from bottle B will be discharged, and Fire Protection APU Button light goes off. Emergency DC 2 provides power to bottle B

Question 4

Answer 4

ELECTRICAL APU GEN BUTTON
– PUSH IN: allows automatic operation of the APU generator
(after APU started)
PUSH OUT: turns APU generator (GEN) OFF. The button is illuminated to indicate that the APU generator is off.

Question 5

Answer 5

APU SHUTOFF BUTTON (GUARDED)
PUSH OUT: normal operation. Fire extinguisher bottle B not armed. The fuel and bleed SOV not commanded to close. If fire detected on APU, red light of APU SHUTOFF Button will illuminate associated with APU FIRE CAS.
PUSH IN: closes the associated fuel and bleed SOV. White light will illuminate to indicate that SOV are commanded closed. Automatically, Fire Protection APU Button light will illuminate to indicate that fire extinguisher bottle armed.

Question 6

Answer 6

2 Modes Auto Brake control:–
Landing mode - pilot may select between 3 deceleration rates . LO, MED, and HI. Auto Brake application will start 1 second after WOW indicates ground and throttle signals idle. Selected deceleration level (HI, MED or LO) will be achieved approximately 1 second after the nose landing gear touch down.

Rejected takeoff mode (RTO). maximum available deceleration rate is selected by turning the AUTO BRAKE Knob to RTO position. RTO mode will apply a demand of brake pressure equivalent to the maximum manual braking.

Question 7

Answer 7

BATT 1 KNOB
ON: BC 1 is closed, connecting HOT BUS 1 to EMER BUS 1
OFF: BC 1 is open, isolating HOT BUS 1 from EMER BUS 1

Question 8

Answer 8

BATT 2 KNOB
AUTO: allows automatic operation of HOT BUS 2. Connects to EMER BUS 2 for normal operation, or isolates from EMER BUS 2 for APU start
OFF: isolates battery 2 from EMER BUS 2

Question 9

Answer 9

FASTEN BELTS SWITCH
ON: turns on FASTEN SEAT BELT sign in passenger cabin
OFF: turns off the FASTEN SEAT BELT sign in passenger cabin

NO SMOKING SWITCH
ON: turns on NO SMOKING sign in passenger cabin
OFF: turns off NO SMOKING sign in passenger cabin

Question 10

Answer 10

BLEED 1 BUTTON
BLEED 1 Button is related to left bleed system.
PUSH IN: normal operation. Automatic operation of LH bleed system. In case of leak detection, BLEED 1 Button amber light illuminates, associated with BLEED 1 LEAK CAS PUSH OUT: manually closes related PRSOV. BLEED 1 Button white light illuminates to indicate PRSOV is commanded closed.
BLEED APU BUTTON
Controls the APU bleed system
PUSH IN: normal operation. Automatic operation of APU bleed system. In case of leak detection, BLEED APU Button amber light illuminates, associated with BLEED APU LEAK PUSH OUT: deactivates APU bleed system. BLEED APU Button white light illuminates to indicate related shutoff valve is commanded closed.
BLEED 2 BUTTON
BLEED 2 Button is related to right (RH) bleed system
PUSH IN: normal operation. Automatic operation of RH bleed system. In case of leak detection, BLEED 2 Button amber light illuminates, associated with BLEED 2 LEAK CAS PUSH OUT: manually closes respective PRSOV. BLEED 2 Button white light illuminates to indicate that PRSOV is commanded closed.

Question 11

Answer 11

BOTTLE BUTTON
PUSH OUT: normal operation. Fire extinguisher bottles not armed. If Engine Fire SHUTOFF 1 Button or Engine Fire SHUTOFF 2 Button pressed, BOTTLE A Button and BOTTLE B Button will illuminate indicating bottles armed.
PUSH IN: discharges associated fire extinguisher bottle agent. Light on pressed button goes off indicating bottle discharged and CAS message of associated bottle will be displayed.

Question 12

Answer 12

BUS TIES SELECTOR
AUTO: allows automatic control of BTC 1, BTC 2, ETC 2, EBC 1 and EBC 2
1 OPEN: opens BTC 1, and allows automatic control of EBC 1, EBC 2 and ETC 2
2 OPEN: opens BTC 2, and allows automatic control of EBC 1, EBC 2 and ETC 2

Question 13

Answer 13

PAX CABIN TEMP CONTROLLER
Controls cabin temperature relative to PAX CABIN Temp Controller position
When knob is turned to C until it clicks, it enters a detent, and temperature control is transferred to VIP seat panel in the cabin.
PUSH IN: automatic temperature control mode
PUSH OUT: manual temperature control mode

Question 14

Answer 14

FIRE PROTECTION CARGO BUTTON (GUARDED)
Momentary action button:– Immediately discharges high rate fire-extinguisher bottle into the cargo compartment and enables metered fire extinguisher bottle to automatically discharge after 2 minutes.
In case of smoke detection in cargo compartment, CARGO SMOKE CAS message will display and Fire Protection CARGO Button light will illuminate, indicating that cargo compartment fire extinguisher bottles shall be discharged.– If pressed again within 2 minutes, starts discharging metered fire extinguisher bottle into cargo compartment

Question 15

Answer 15

COCKPIT TEMP CONTROLLER
Controls cockpit temperature relative to COCKPIT Temp Controller position
PUSH IN: automatic temperature control mode
PUSH OUT: manual temperature control mode

Question 16

Answer 16

DOWNLOCK RELEASE BUTTON
DN LCK REL Button mechanically bypasses system protection logic. Should be used only in the event of a LDG GEAR Lever failure, or when necessary to clear obstacles.

Question 17

Answer 17

DUMP BUTTON (GUARDED)
Provides rapid cabin depressurization by opening outflow valve, and commands cabin inflow and recirculation fan to off.
PUSH IN: dump function is activated and white bar illuminates across button
PUSH OUT: system returns to normal.
NOTE: When operating in manual mode, outflow valve will also be commanded open

Question 18

Answer 18

EDP SHUTOFF BUTTON (GUARDED)
PUSH OUT: normal operation. SOV is open and operating
PUSH IN: closes SOV, isolating respective engine driven pump (EDP). Button will illuminate

Question 19

Answer 19

ELEC EMER BUTTON (GUARDED)
PUSH IN: opens EBC 1 and EBC 2, and closes ETC 2, isolating EPDC 1 and EPDC 2 from LPDC and RPDC
PUSH OUT: power contactors operate automatically according to electrical distribution logic.
NOTE: ELEC EMER Button is illuminated when button is pushed in

Question 20

Answer 20

ELT SELECTOR
ON: activates ELT
ARMED: allows ELT to be automatically activated
TEST/RESET: RESET function allows ELT deactivation after manual or automatic activation.
RED LIGHT
After the test:
A series of short flashes indicates that the test has failed
One long flash indicates a successful test.
Periodic flashes during 121.5/243.0 MHz transmission
Long flashes during 406 MHz transmission

Question 21

Answer 21

EMER LT SELECTOR
OFF: turns off emer lights to prevent emergency lights batteries from being drained
ARMED: emergency lights stay off and emergency light batteries are continuously charged. Lights automatically turn on if normal airplane power is lost due to electrical emergency, or if airplane is subjected to an impact
ON: turns on emergency lights, powered by emergency light system batteries

Question 22

Answer 22

ENG START/STOP SELECTOR
STOP: commands FADEC to shut down corresponding engine
RUN: normal selector position for engine operation
START (momentary action): initiates engine start sequence

Question 23

Answer 23

EVENT MARKER BUTTON
Allows FADEC to record data for investigation when flight crew identifies an engine condition that may require maintenance, but with no clear fault. FADEC records for 3 minutes (2 minutes before and 1 minute after EVENT MARKER Button is pressed)

Question 24

Answer 24

ENGINE FIRE SHUTOFF BUTTON (GUARDED)
PUSH OUT: normal operation. Fire extinguisher bottles not armed. If fire detected on engine, red light of affected engine will illuminate. Associated with ENG 1 (2) FIRE CAS message and FIRE inscription on ITT indication of EICAS
PUSH IN: closes associated fuel, hydraulic and bleed SOV. White light will illuminate to indicate SOV are commanded to close. Automatically, BOTTLE A Button and BOTTLE B Button lights will illuminate to indicate fire extinguisher bottles are armed

Question 25

Answer 25

FIRE PROTECTION TEST BUTTON (PRESS AND RELEASE) It starts fire and smoke detection system test. Verifying proper button lamp function, aural warning, FIRE icon on ITT display, and CAS messages, by simulating fire condition. Checks only cockpit visual and aural indications, not fire detectors nor fire extinguisher bottle faults. NOTE: test runs for 10 seconds. If APU is running, be aware that two consecutive tests, within 15 seconds, may shutdown APU FIRE PROTECTION ANNUNCIATOR TEST BUTTON Illuminates all annunciator lights

Question 26

Answer 26

FLAP OVRD BUTTON Disregards flaps position for calculations of GPWS mode 2 (excessive closure rate of terrain), GPWS mode 3 (negative climb rate after takeoff), and GPWS mode 4 (flight into terrain when not in landing configuration)

Question 27

Answer 27

NORMAL MODE BUTTON (GUARDED) Button installed on center pedestal panel to recover NM or to revert to DM in case of NM misbehavior. Manual reversion to DM is inhibited while the following FCS envelope protections are engaged: Low speed protection, Angle Of Attack (AOA) limiter protection, High speed protection.

Question 28

Answer 28

FUEL PUMP SELECTOR OFF: deactivates the associated fuel pumps AUTO: A Pumps Activated. B Pumps automatically operate during ENG Start, APU Start or Run, Low Fuel Pressure, Xfeed and A Pump Failure ON: activates the associated fuel pumps NOTE: Setting the Fuel PUMP 1 Selector or Fuel PUMP 2 Selector to any position different than AUTO overrides fuel Xfeed command

Question 29

Answer 29

GALLEY MASTER BUTTON (GUARDED) PUSH IN: enables passengers to use electrical equipment installed in galley PUSH OUT: turns off all electrical equipment installed in galley, MASTER button light will be illuminated. GALLEY LIGHTS SWITCH AUTO: enables commands to galley lights through CMS controller OFF: turns off all galley lights, independently of CMS controller

Question 30

Answer 30

WRN INHIB BUTTON Inhibits landing gear aural warning when landing flaps not selected, radio altimeters are not operational, and TLA is set to idle.

Question 31

Answer 31

GEN 1 SELECTOR AUTO: allows automatic control of Generator Line Contactor (GLC) 1, connecting GEN 1 to DC BUS 1 OFF: turns GEN 1 OFF

Question 32

Answer 32

GND PROX TERR INHIB BUTTON Deactivates Forwarding Looking Terrain Avoidance (FLTA), Forwarding Looking Obstacle Alerting (FLOA), and Premature Descent Alert (PDA) aural and visual alerts

Question 33

Answer 33

GPU BUTTON PUSH OUT: GPU not allowed to provide power to airplane. If GPU is connected and its voltage is 25V-30V, AVAIL button white light will illuminate PUSH IN: Connects GPU to airplane buses, providing power to airplane. IN USE button green light will illuminate and AVAIL button white light goes off. NOTE:– If APU is started while airplane is powered by GPU, APU becomes source of power, GPU is disabled and button lights (AVAIL and IN USE) go off. GPU indication remains displayed on ELEC synoptic to indicate that GPU is still connected. Make sure that GPU indication is removed from ELEC synoptic before taxi.

Question 34

Answer 34

G/S INHIB BUTTON Deactivates GPWS mode 5 (excessive downward deviation from an ILS glide slope) aural and visual alerts.

Question 35

Answer 35

ICE PROT ENG BUTTON PUSH-IN: enables operation of associated engine ice protection system. It opens associated engine anti-ice pressure regulating shutoff valve (EAIV) PUSH-OUT: deactivates associated engine ice protection system. It closes associated EAIV. Center indicator illuminates white

Question 36

Answer 36

ICE PROT TEST BUTTON Momentary action button: performs wing and horizontal stabilizer anti-icing system functionality verification manually on ground NOTE: Test is normally accomplished automatically during power up. Test duration is about 35 seconds. Can be manually initiated.

Question 37

Answer 37

ICE PROT WINGSTAB BUTTON PUSH-IN: enables operation of wing and horizontal stabilizer anti-icing system. Opens wing and horizontal stabilizer anti-ice shutoff valve (AISOV) PUSH-OUT: deactivates wing and horizontal stabilizer anti icing system. Closes AISOV. Center indicator illuminates white. NOTE: Center indicator illuminates amber associated with A-I WINGSTAB LEAK CAS in case of anti-ice bleed air leak

Question 38

Answer 38

ICE PROT MODE KNOB ICE SPEED RESET: momentary position that resets stall protection to non-icing condition settings and removes STALL PROT ICE SPEED CAS NOTE: ICE SPEED RESET must be activated when pilot is sure no more ice on airplane, including wing leading edges (wing tip) and windshield unprotected areas. AUTO: enables automatic activation of wing and horizontal stabilizer anti-icing system and engine ice protection system by ice detectors. NOTE: Wing and horizontal stabilizer anti-icing system and engine ice protection system are activated as soon as an icing condition is detected, whenever airplane is above 1700 ft AGL or 2 minutes in air, whichever occurs first. ENG: Activates engine ice protection system on ground and in flight, overriding ice detectors. NOTE: In flight, it keeps automatic activations of wing and horizontal stabilizer anti-icing system by ice detectors. ALL: Activates wing and horizontal stabilizer anti-icing system and engine ice protection system, overriding ice detectors. NOTE: On ground, below 30 kt, only engine ice protection system is activated. Above 30 kt, wing and horizontal stabilizer anti-icing system and engine ice protection system are activated, regardless indication of ice detection system.

Question 39

Answer 39

IFE BUTTON PUSH IN: enables passengers to command IFE System through CMS controller PUSH OUT: turns off In-Flight Entertainment System. IFE light will illuminate.

Question 40

Answer 40

IGNITION KNOB OFF: Deactivates ignition system on ground AUTO: FADEC automatically controls ignition system depending on engine requirements. Additionally, auto ignition is provided in response to engine flameout detection or imminent airplane stall conditions ON: Enables system test and continuous ignition

Question 41

Answer 41

LAV DOOR SWITCH OPEN: after 5 seconds, electrically opens the Lavatory Pocket Door and lock the door at open position CABIN CTRL: enables the passengers to control the Lavatory Pocket Door freely

Question 42

Answer 42

OUTLETS SWITCH ON: turns on the AC power to the outlets on the passenger cabin OFF: turns off the AC power to the outlets on the passenger cabin

Question 43

Answer 43

OXYGEN SELECTOR CREW ONLY: Disables automatic deployment of passenger oxygen masks PAX AUTO: Enables automatic deployment of passenger oxygen masks when cabin pressure altitude is above 14500 ft (+/- 300 ft) PAX OVRD: Deploys passenger oxygen masks regardless of cabin altitude. NOTE: When OXYGEN Selector is moved to PAX OVRD position CABIN ALTITUDE HI CAS message is displayed. If airplane is above 25.000 ft and autopilot is engaged EDM will be activated.

Question 44

Answer 44

PACK BUTTON Controls pack operation PUSH IN: Normal operation. Automatic operation of air conditioning. This position allows pack flow control valve to open. In case of leak detection, PACK Button amber light will illuminate associated with PACK LEAK CAS PUSH OUT: Manually closes pack flow control valve. PACK Button white light will illuminate to indicate that shutoff valves are commanded closed PACK BACKUP BUTTON Controls the operation of the backup if there is a failure of the pressurization and air conditioning kit (PACK) PUSH IN: normal operation. Automatic operation of pack backup PUSH OUT: deactivates pack backup. PACK BACKUP Button white light will illuminate to indicate that shutoff valve is commanded to close.

Question 45

Answer 45

PITCH SWITCH For trim purposes there is a dual switch for pitch axis trim adjustment. Both switches must be simultaneously actuated in the same direction to provide command to the PTS The PTS can be manually commanded only on ground or in DM

Question 46

Answer 46

PRESSURIZATION MODE BUTTON (GUARDED) PUSH OUT: automatic control of pressurization system PUSH IN (illuminated): manual control of pressurization system through CABIN ALT knob. CABIN ALT CONTROLLER DN: manually closes outflow valve, decreasing cabin altitude rate in 50 ft/min steps Vertical Position: normal operation position, no movement on outflow valve UP: manually opens outflow valve, increasing cabin altitude rate in 50 ft/min steps NOTE: Manual actuation of outflow valve is possible only with Pressurization MODE Button set at pushed in position.

Question 47

Answer 47

PTU KNOB OFF: deactivates PTU 1: allows PTU to transfer hydraulic power from hydraulic system 2 to hydraulic system 1 AUTO: allows PTU to operate automatically 2: allows PTU to transfer hydraulic power from hydraulic system 1 to hydraulic system 2

Question 48

Answer 48

RECIRC KNOB Controls both recirculation fans operation and speed mode OFF: turns off recirculation fan LO: selects low speed mode for recirculation fan AUTO: automatic operation of recirculation fan HI: selects high speed mode for recirculation fan.

Question 49

Answer 49

ADS BUTTON Use to manually change ADS source of left and right PFD. Left PFD normally uses ADS 1 as its air data source, while right PFD normally uses ADS 2. ATT HDG BUTTON Attitude and heading source of PFD can be manually changed through ATT HDG Button. EICAS BUTTON Pilot or copilot can revert EICAS window to their PFD, as preferred

Question 50

Answer 50

SMS INHIB BUTTON Inhibits aural and visual alerts of Surface Management System, but not chart runway highlight. CAS message SMS INHIBIT will be displayed

Question 51

Answer 51

STEERING BUTTON (MOMENTARY ACTION) When button is illuminated, steering engagement is enabled NOTE: light on STEERING Button and STEERING DISC CAS message can take up to 2 seconds to go off after first engagement of steering If external STEERING DISENGAGE switch is on DISENGAGE position, pilot will not be able to engage steering system through STEERING Button in cockpit. STEERING DISC CAS message will be displayed and STEERING Button in cockpit will not be illuminated.

Question 52

Answer 52

SYS 1 ELEC PUMP KNOB ON: operates electrical pump continuously, overriding hydraulic system logic OFF: turns associated electrical pump off AUTO: allows automatic operation of electrical pump During takeoff, DCMP 1 is automatically commanded to start when at least one of THRUST Levers is TO/GA position or higher TLA. During landing, DCMP 1 is automatically commanded to start when: -Both THRUST Levers are in landing configuration (close to IDLE position) -Landing gear commanded to extend -Airplane speed greater than 50 kt

Question 53

Answer 53

SYS 3 ELEC PUMP KNOB OFF: turns associated electrical pump off ON: turns associated electrical DCMP 3 is only power source for Hydraulic System 3 and is powered by EMER BUS 3. Hydraulic System 3 supplies following systems: -Elevator (RH outboard actuator) -Rudder (lower actuator) -Multifunction spoilers (LH and RH pane)

Question 54

Answer 54

TO CONFIG BUTTON Checks if airplane is in takeoff configuration. Voice message “TAKEOFF OK” is generated when airplane config is suitable for takeoff. If aircraft config is not suitable for takeoff, aural warning will sound and NO TAKEOFF CAS will display. Warning will be activated for any of following conditions: * Parking brakes applied * Any spoiler panel deployed * Flaps not in takeoff position * Pitch trim out of green range BRAKES BE SPOILER SAFE FLAPS FIRST TRIM TIME

Question 55

Answer 55

Water drainage system allows draining of remaining water simultaneously from lavatory potable water tank by pressing WATER DRAIN Button, while SHED BUS 1 is energized. Once button is pressed and released, drain valve opens and pumps are powered on until tank empty. If tank full (3.9 gal), process can take 10 min to drain both tank and hose.

Question 56

Answer 56

WINDSHIELD BUTTON PUSH-IN: enables operation of associated windshield heating system PUSH-OUT: deactivates associated windshield heating system. Center indicator illuminates white. Windshield heater control units (WHCU) begin to control and monitor windshield heaters as soon as aircraft is powered up. If windshield temp is below 30°C, heating elements will turn on, and when temp reaches 45°C, they turn off. To manually deactivate windshield heat, push out windshield LH or RH buttons on heaters panel. In certain emergency/abnormal conditions, windshield heating system may be fed by a single generator and operate in power-saving mode. This will only supply power to one heater on LH windshield. Windshield heating system does not operate if fed by batteries only.

Question 57

Answer 57

XBLEED BUTTON Controls cross bleed valve operation. PUSH IN: normal operation. Automatic operation of cross bleed valve PUSH OUT: manually closes cross bleed valve. XBLEED Button white light will illuminate to indicate that shutoff valve is commanded to close

Question 58

Answer 58

FUEL XFEED KNOB LO 1: opens crossfeed valve and automatically deactivates operating fuel pump 1 (A or B), supplying fuel to both engines and APU from RH wing tank OFF: closes crossfeed valve LO 2: opens crossfeed valve and automatically deactivates operating fuel pump 2 (A or B), supplying fuel to both engines and APU from LH wing tank. NOTE: XFEED operation is not allowed during takeoff, go around and landing flight phases

Question 59

Answer 59

YAW CONTROLLER– For trim purposes there is one controller for yaw axis trim adjustment (left/right)