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85 Cards in this Set
- Front
- Back
Dome Light Switch
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Batteries must be ON/AUTO to have dome lights on
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CVR Erase
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Must be on the ground with parking brake set
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DVDR Test
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Self test of DVDR 1 and DVDR 2. Failure is indicated by CVR AFT(FWD) Fail
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IDG 1 and IDG 2 Selector Knob
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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 |
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Normal AC Bus Source Priority
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Respective IDG, then AC Bus Tie
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When does IDG LED Illuminate?
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IDG 1(2) Oil caution
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AC Bus Ties Selector Knob
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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 |
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AC BUS TIE Priority
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APU
GPU IDG |
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GPU Button
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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 |
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GPU Avail Light
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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.
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GPU IN USE Light
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Will only illuminate when the button is pushed in, and the AC GPU is powering the AC BUS TIE
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APU GEN Button
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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 |
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TRU ESS Toggle Switch
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AUTO: allows for automatic connection of the TRU ESS to the ESS BUS 3
OFF: Isolates the TRU ESS from the ESS BUS 3 |
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TRU 1 and TRU 2 Toggle Switch
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Auto: Allows automatic connection of the TRU to the respective DC BUS
OFF: Isolates the TRU from the respective DC BUS |
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Batt 1 Selector Knob
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ON: Battery is connected to the DC ESS BUS 1
OFF: Battery supplies to HOT BATT BUS 1 only |
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DC BUS TIES Toggle Switch
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AUTO: Allows automatic operation of the DC TIE contactors (1DCTC/2ETC's) according to system logic
OFF: Opens all DC TIE contactors |
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BATT 2 Selector Knob
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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 |
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Fuel XFEED Selector Knob
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Low 1: Opens the cross feed valve, and activates AC Pump 2 to supply fuel to both engines from the right wing tank
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DC PUMP
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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 |
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AC PUMP 1 and AC Pump 2
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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. |
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EMER LT Selector Knob
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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. |
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#1 and #2 Engine Fire EXTG Handle
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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 |
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APU Swiitch (Guarded)
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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 |
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Cargo Smoke FWD and AFT buttons in Flight
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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. |
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Cargo Smoke FWD and AFT buttons on Ground
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(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. |
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Fire Detection System TEST Button
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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 |
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APU MASTER Knob
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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 |
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EMER STOP Button (Guarded)
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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. |
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PTU Switch
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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 |
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SYS 1 and SYS 2 ENG PUMP SHUTOFF Buttons
(Guarded) |
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. |
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SYS 1 and SYS 2 ELEC PUMP Selector Knobs
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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 |
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SYS 3 ELEC PUMP A Selector Knob
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OFF: Turns the electrical pump off.
ON: Operates the electrical pump continuously |
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SYS 3 ELEC PUMP B Selector Knob
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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. |
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Pressurization MODE Selector Knob
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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 |
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DUMP Button (Guarded):
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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 |
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CAB ALT Selector Knob
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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 |
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LFE Knob
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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 |
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WINDSHIELD HEATING BUTTON 1 and 2
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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. |
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WING ICE PROTECTION Button
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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. |
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ENGINE ICE PROTECTION Button
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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. |
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ICE PROTECTION MODE Selector Knob
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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. |
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Pneumatic source priority?
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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. |
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RECIRC Button
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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 |
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PACK 1 and PACK 2 Buttons
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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 |
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XBLEED Button
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PUSH IN: Allows the AMS to control automatic operation of the cross bleed valve.
PUSH OUT: Manually closes the cross bleed valve |
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BLEED 1 and BLEED 2 Buttons
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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 |
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APU BLEED Button
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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 |
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MASKS DEPLOY Knob
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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. |
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MASKS DEPLOYED Indicator
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An ON light illuminates, indicating that the passenger and
flight attendant oxygen masks have been commanded to deploy |
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#1 and #2 WINDSHIELD WIPER Controls
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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 |
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ADS Button
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Manually reverts the ADS source
Reversion to ADS 3 is automatic |
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IRS Button
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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 |
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AUTOBRAKE Selector Knob
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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 |
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Autobrake Wheel Speed
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60 knots
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GND PROX TERR INHIB Pushbutton
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When pressed, inhibits EGPWS and thus avoids unwanted
terrain alerts in airports not covered by EGPWS database |
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EMERG/PRKGBRAKE Light
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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. |
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EICAS Declutter
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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 |
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GND PROX G/S INHIB Button
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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 |
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LG WRN INHIB Button
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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 |
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DUMP Button
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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 |
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HEATER Button
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PUSH IN: Activates the ADS probes heater. A white striped
bar illuminates. PUSH OUT: The ADS probes heater works in AUTO mode |
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START/STOP Selector Knob
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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 |
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IGNITION Selector Knob
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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 |
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FLIGHT CONTROLS MODE Buttons (GUARDED)
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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 |
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SHAKER CUTOUT Button
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PUSH IN: Cuts out the associated yoke shaker channel.
PUSH OUT: Allows normal operation of the stick shaker |
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T/O CONFIG Button
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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 |
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EICAS FULL Button
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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 |
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Speedbrake Lever
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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 |
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Thrust Levers
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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. |
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Flap Override Switch (GUARDED)
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Inhibits triggering of flap alerts in case of landings where flap
configuration is other than 5 or FULL. |
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MIC/MASK Switch
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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 |
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BKUP VOL Switch
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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 |
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SELCAL Button
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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. |
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TRIM Panel
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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 |
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SYS 1 CUTOUT Switch (GUARDED)
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PUSH IN: Disables pitch trim channel 1.
PUSH OUT: Enables pitch trim channel 1 |
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LOCK Pushbutton (GUARDED)
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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 |
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INHIB Pushbutton (MOMENTARY ACTION)
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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 |
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UNLOCKED Indicator
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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 |
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ELEVATOR DISCONNECT Handle
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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 |
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AILERON DISCONNECT Handle
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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. |
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Alternate Gear Extension Lever (Two Position)
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When pulled releases all hydraulic fluid from the landing gear
lines and releases all landing gear uplocks |
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Electrical Override Switch
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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). |
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TO on FMA during taxi/ takeoff
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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. |
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HOLD on FMA
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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. |
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TRACK on FMA
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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 |