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Front Back
COCKPIT LIGHTS Panel

1. MAIN PNL Knob
Turns on/off and sets the lighting brightness of the Guidance
Panel and Instrument Panel background lighting.
COCKPIT LIGHTS Panel

2. OVHD PNL Knob
Turns on/off and sets the brightness of the overhead panel’s
background lighting. Rotating the knob to the OFF position
will illuminate all annunciator lights to full bright.
COCKPIT LIGHTS Panel

3. PEDESTAL Knob
Turns on/off and sets pedestal lighting brightness.
COCKPIT LIGHTS Panel

4. DOME Light Switch
Turns on/off the two cockpit dome lights. Batteries must be
ON/AUTO to have dome lights on.
COCKPIT LIGHTS Panel

5. ANNUNCIATORS TEST Button
The striped bars and caption indications in all main panel, overhead panel, and control pedestal pushbuttons illuminate when pressed, allowing verification of lamp integrity. TheEMRG/PRKG BRAKE light, Master Warning and Master Caution, GPU pushbutton light, and fire test lights are not
illuminated.
DVDR CONTROL PANEL

1. CVR ERASE
Allows CVR data to be erased when the aircraft is on the ground with the parking brake set.
DVDR CONTROL PANEL

2. DVDR TEST
Commands a self test of DVDR 1 and DVDR 2. A failure is indicated by a CVR AFT(FWD) FAIL advisory message on the EICAS.
DVDR CONTROL PANEL

3. HEADPHONE Jack
Allows a headset to be inserted to monitor the composite audio output of the DVDR unit during tests and normal operations.
DVDR CONTROL PANEL

4. Selector Switch
FWD: Enables the test tone of DVDR 1 to be heard when a headset is plugged in to the headphone jack.

AFT: Enables the test tone of DVDR 2 to be heard when a headset is plugged in to the headphone jack.
ELECTRIC Panel

1. IDG 1 and IDG 2 Selector Knob
AUTO: This position allows the 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 AC BUS.
DISC: Must be held in this position for one second to mechanically disconnect the IDG. The IDG cannot be reconnected in flight.
NOTE 1: Normal AC BUS source priority is on-side IDG, AC BUS TIE, off-side IDG.
NOTE 2: The illumination of an amber LED next to the DISC position of the IDG 1 or IDG 2 rotary knob indicates to the pilot which IDG to disconnect. This LED will illuminate in association with the IDG 1(2) OIL caution EICAS, and will extinguish after the IDG is disconnected.
ELECTRIC Panel

2. AC BUS TIES Selector Knob

1 OPEN: Opens the Bus Tie Contactor (BTC) 1, segregating AC BUS 1 from the AC BUS TIE.
AUTO: This position allows automatic operation of the BTC’s according to system logic.
2 OPEN: Opens the Bus Tie Contactor (BTC) 2, segregating AC BUS 2 from tthe AC BUS TIE.
NOTE: AC BUS TIE source priority is APU, GPU, then IDG.
ELECTRIC Panel

3. GPU Button

PUSH IN: Connects the AC GPU to the AC BUS TIE, according to the source priority.
PUSH OUT: Isolates the AC GPU from the AC BUS TIE.
NOTE: AVAIL Light: AVAIL will illuminate with the button pushed in or out when the AC GPU is connected to the aircraft, but is not powering the AC BUS TIE.
IN USE Light: IN USE will only illuminate when the button is pushed in, and the AC GPU is powering the AC BUS TIE.
ELECTRIC Panel

4. APU GEN Button
PUSH IN: This position allows the APU generator to connect to the AC BUS TIE, automatically according to the 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.
ELECTRIC Panel DC POWER

5. TRU ESS Toggle Switch
AUTO: This position allows automatic connection of the TRU ESS to the ESS BUS 3.
OFF: Isolates the TRU ESS from the ESS BUS 3.
ELECTRIC Panel DC POWER

6. TRU 1 and TRU 2 Toggle Switch
AUTO: This position allows automatic connection of the TRU to the respective DC BUS.
OFF: Isolates the TRU from the respective DC BUS.
ELECTRIC Panel DC POWER

7. BATT 1 Selector Knob
ON: The battery is connected to the DC ESS BUS 1.
OFF: The battery supplies power to HOT BATT BUS 1 only.
ELECTRIC Panel DC POWER

8. DC BUS TIES Toggle Switch
AUTO: This position allows automatic operation of the DC TIE contactors (1 DCTC/2ETC’s), according to system logic.
OFF: Opens all DC TIE contactors.
ELECTRIC Panel DC POWER

9. BATT 2 Selector Knob
AUTO: This position 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.
FUEL Panel

1. XFEED Selector Knob
LOW 1: Opens the cross feed valve, and activates AC PUMP 2 to supply fuel to both engines from the right wing tank.
OFF: Closes the crossfeed valve.
LOW 2: Opens the cross feed valve, and activates AC PUMP 1 to supply fuel to both engines from the left wing tank.
FUEL Panel

2. DC PUMP
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.
FUEL Panel

3. AC PUMP 1 and AC PUMP 2
OFF: Deactivates the associated AC PUMP.
AUTO: Allows automatic operation of the associated AC PUMP in accordance with system logic.
ON: Activates the associated AC PUMP.
NOTE: 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.
PASSENGER SIGNS Panel

1. 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.
PASSENGER SIGNS Panel

2. ATTND CALL Button
Pressing this button sounds a chime in passenger cabin, and illuminates the green light on the Flight Attendant rainbow.
PASSENGER SIGNS Panel

3. FSTN BELTS Toggle Switch
ON: Illuminates the FASTEN BELTS signs. Turning the switch ON sounds a single low tone chime in the cabin,
lavatories, and galleys.
OFF: Turns off the FASTEN SEAT BELTS signs. Turning the switch OFF sounds a single low tone chime in the cabin.
NOTE: The Fasten Seat Belts sign will automatically illuminate when masks are commanded to deploy.
PASSENGER SIGNS Panel

4. NO SMKG Toggle Switch
ON: Illuminates the NO SMOKING signs. Turning the switch ON sounds a single low tone chime in the cabin.
OFF: Turns off the NO SMOKING signs. Turning the switch OFF sounds a single low tone chime in the cabin.
NOTE: The No Smoking sign will automatically illuminate when the oxygen masks are commanded to deploy.
PASSENGER SIGNS Panel

5. STERILE Toggle Switch
(Not used at Jetblue)
ON: Illuminates the amber sterile light on the flight attendant rainbow. Turning the switch ON sounds a single high tone chime in the cabin.
OFF: Turns off the amber sterile light on the flight attendant rainbow.
FIRE EXTINGUISHER Panel

1. #1 and #2 Engine Fire EXTG Handle:
Illuminates when fire is detected.
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.
FIRE EXTINGUISHER Panel

2. APU (Guarded)
Momentary action pushbutton.
Closes the APU fuel shutoff valve and discharges the APU fire extinguisher bottle. The light will illuminate when the APU EMER STOP button has been pushed in when an APU fire has been detected, 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.
FIRE EXTINGUISHER Panel

3. CARGO SMOKE FWD and AFT Buttons (GUARDED) Smoke Detected In flight

Momentary action pushbutton. Illuminates when the high rate
bottle is armed.
smoke detected
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
IN FLIGHT: a single button
push will arm the HIGH rate
bottle. A second button push
will discharge the HIGH rate
bottle. 60 seconds later the
LOW rate bottle will discharge.
FIRE EXTINGUISHER Panel

3. CARGO SMOKE FWD and AFT Buttons (GUARDED) Smoke Detected on Ground
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.
ON GROUND: a single button push will arm the HIGH rate bottle. A  second push will discharge the HIGH rate bottle. A third button push will
discharge the LOW rate bottle.
NOTE: In flight or on ground, with no smoke detected, if either cargo smoke fire extinguisher button is pushed inadvertently, push the test button to cancel or wait two
minutes for the system to reset automatically.
FIRE EXTINGUISHER Panel

4. Fire Detection System TEST Button

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.
FIRE EXTINGUISHER Panel

4. Fire Detection System TEST Button
Messages

AURAL WARNING - FIRE BELL/TRIPLE CHIME
Overhead Panel (6)
  • Engine 1 and 2 fire EXTG handles illuminate
  • FWD and AFT CARGO SMOKE pushbuttons illuminate
  • APU fire extinguisher pushbutton illuminates
  • Red bar in APU EMER STOP pushbutton illuminates
EICAS (5)
  • ENG 1 FIRE
  • ENG 2 FIRE
  • APU FIRE
  • CARGO FWD SMOKE
  • CARGO AFT SMOKE
GLARESHIELD PANEL/EICAS (4)
  • Master Warning Lights illuminated
  • FIRE icon on engine 1 and 2 ITT gauges
APU CONTROL Panel

1. MASTER Knob
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, the MASTER rotary knob can be moved from OFF back to ON and the APU will continue running.
APU CONTROL Panel

2. EMER STOP Button (Guarded)
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.
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.
HYDRAULIC System Panel

1. PTU Switch
OFF: Turns the PTU off.
AUTO: During takeoff or landing with the flaps not at zero, the PTU will activate with a failure of ENG 2 or the ENG 2 Engine Driven Pump (EDP) to provide normal landing gear
extension and retraction.
ON: The PTU operates continuously.
HYDRAULIC System Panel

2. 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.
HYDRAULIC System Panel

3. SYS 1 and SYS 2 ELEC PUMP Selector Knobs
OFF: Turns the associated electrical pump off.
AUTO: On Ground: SYS 1 and SYS 2 will run automatically for takeoff when the flaps are not set at zero; and the thrust levers are advanced beyond 60 degrees of TLA, 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 when flaps are not at zero.
ON: Operates the electrical pump continuously.
HYDRAULIC System Panel

4. SYS 3 ELEC PUMP A Selector Knob
OFF: Turns the electrical pump off.
ON: Operates the electrical pump continuously.
HYDRAULIC System Panel

5. SYS 3 ELEC PUMP B Selector Knob
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.
PRESSURIZATION Panel

1. Pressurization MODE Selector Knob
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.
PRESSURIZATION Panel

2. DUMP Button (Guarded):
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. 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.
PRESSURIZATION Panel

3. CAB ALT Selector Knob
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.
PRESSURIZATION Panel

4. LFE Knob
Manual input of the LFE is only possible when the pressurization MODE knob is selected to LFE.
DOWN: Decreases the LFE in 100’ increments. If held longer than 5 seconds the LFE will decrease in 500’ increments.
STOP (Spring Loaded): Normal operation position.
UP: Raises the LFE in 100’ increments. If held longer than 5
seconds the LFE will increase in 500’ increments.
ICE PROTECTION Panel

1. WINDSHIELD HEATING BUTTON 1 and 2
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.
ICE PROTECTION Panel

2. WING ICE PROTECTION Button
PUSH IN: Allows automatic operation of the wing anti-ice system.
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.
ICE PROTECTION Panel

3. ENGINE ICE PROTECTION Button
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.
ICE PROTECTION Panel

4. ICE PROTECTION MODE Selector Knob

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.
ICE PROTECTION Panel

5. ICE PROTECTION TEST Knob
ENG: Provides a test for the engine anti-ice system.
OFF: Spring-loaded position.
WING: Provides a test for the wing anti-ice system.
NOTE: Operation of this switch will be a function of Technical Operations.
ICE PROTECTION Panel

TO DATASET MENU - OFF
MODE SELECTOR KNOB - AUTO
ICE CONDITION NOT DETECTED - N/A
ICE CONDITION Detected
ENGINE A/I ACTIVIATION
ON: 1700’ AGL or 2 min after liftoff
OFF: 5 min after ice condition no longer detected
WING A/I ACTIVATION
ON: 1700’ AGL or 2 min after liftoff
OFF: 5 min after ice condition no longer detected
ICE PROTECTION Panel

TO DATASET MENU - OFF
MODE SELECTOR KNOB ON
ICE CONDITION Detected and Not Detected
ENGINE A/I ACTIVIATION
ON: Engine Running
OFF: Engine shutdown
WING A/I ACTIVATION
ON: Liftoff
OFF: Touchdown
EICAS CAUTION MESSAGE
ENG REF A/I DISAG
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