GUIA DE ESTUDOS PARA PROVA ORAL DVDR CONTROL
ELECTRICALELECTRICAL FUEL FIRE PROTECTIONAPU CONTROL HYDRAULIC
COCKPIT LIGHTS PASSENGER SIGNS WINDSHIELD WIPERS EXTERNAL LIGHTING
ICE PROTECTION ECS/PNEUMATICECS/PNEUMATIC PRESSURIZATIONPASSENGER
OXYGEN AKD 2010
Slide 3
DVDR CONTROL Selector Swicht : Enable to test the tone of the
DVDR 1 (FWD) or DVDR 2 (AFT) to be heard when a headset in plugged
in to the jack. HEADPHONE Jack : Allows a headset to be insert to
monitor the composite audio output of the DVDR unit during tests
and normal operations. DVDR TEST: Commands a self test of DVDR 1
and 2. EICAS advisory message - CVR AFT (FWD) FAIL DVDR ERASE :
Allows CVR data to be erase when the aircrafts is ON THE GROUND
with the PARKING BRAKE SET 1- What are you checking for when you
press the test button? Verify no fail displayed on EICAS.
Slide 4
ELECTRICAL (AC) IDG 1 and 2 Selector Knob: GROUND POWER UNIT
(GPU) BUTTON : PUSHED IN Conects the AC GPU to the AC BUS TIE,
according to the source priority PUSHED OUT Isolates the AC GPU
from the AC BUS TIE AVAIL light illuminates when the AC GPU is
properly connected and the AC power requirements are satisfied. IN
USE light pushed in / AC GPU is powering AC BUS TIE PUSH IN -
Allows automatic operatio of the electrical system. This position
connects the APU generator to the AC BUS TIE according to the
source priority. PUSH OUT - Opens the APU generator conector and
isolates the APU generator from the AC BUS TIE. The APU generator
is tripped off and de-excited.
Slide 5
ELECTRICAL (DC) BATT 1 Selector Knob: ON- Batt connected to DC
ESS BUS 1. OFF- Batt supply HOT BATT BUS. BATT 2 Selector Knob:
AUTO Allows automatic operation of the electrical system. Connects
Batt 2 to the DC ESS BUS 2. OFF The battery supplies power to the
HOT BATT BUS 2 only. DC BUS TIE Toggle Switch: AUTO Allows
automatic operation of the electrical system. This position
controls the operation of the DC Tie Contactors (ETCs/DCTC).
According to the system logic. OFF Opens all tie contactors. 2-
What is the minimum voltage? 22.5 VDC. TRU ESS Toggle Switch: AUTO
Allows automatic operation of the electrical system. This position
connects the TRU ESS to the ESS BUS 3. OFF Isolates the TRU ESS
from the ESS BUS 3. TRU 1 and TRU 2 Toggle Switch: AUTO Allows
automatic operation of the electrical system. This position
connects the TRU to the respective DC BUS. OFF Isolates the TRU
from the respective DC BUS. 1 - Why is there an AUTO position on
BATT 2? BATT 2 supplies the APU START BUS during APU starting.
Supplies the FADEC.
Slide 6
COCKPIT LIGHTS Panel PEDESTAL Knob: Turns ON/OFF and sets
pedestal lighting brightness. DOME Light Switch: Batteries must be
ON/AUTO to have DOME lights ON. ANNUNCIATORS TEST Button: Olnly the
EMRG/PRKG BRAKE light, GPU pushbutton light, and fire test lights
are not illuminated. MAIN PNL Knob: Turns ON/OFF and sets the
lighting brightness Of the Guidance Panel (GP) and instrument Panel
Background lighting. The stripe bars and caption indications in all
main panel, overhead panel and control pedestal pushbuttons
Illuminate when pressed, allowing verification of lamp integrity.
OVHD PNL Knob: Turns ON/OFF and sets the brightness of The Overhead
Panels background lighting. Rotating the knob to the OFF position
will Illuminate all annunciator lights to full bright. 1 - What are
you checking for when you push the ANNUNCIATOR PANEL TEST Button?
The lamp integrity of all striped bars and caption indication of
all main panel, overhead panel, and control pedestal.
Slide 7
FUEL Panel XFEED Selector Knob: LOW 1 Opens the xfeed valve,
and activates AC PUMP 2 to supply fuel to both engines from the
right wing tank. OFF Closes the xfeed valve. LOW 2 Opens the xfeed
valve, and activates AC PUMP 1 to supply fuel to both engines from
the left wing tank. DC PUMP: OFF Deactivates the DC fuel pump AUTO
Allows automatic operation of the DC PUMP in accordance with S.L.
ON Activates the DC fuel pump. If the APU is inoperative and no AC
ground power is avbl, the DC FUEL PUMP will be used for initial
fuel supply. The DC PUMP is not a backup for the AC pump. 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
S.L. (system logic) ON Activates the associated AC PUMP 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 operation. LIMITATION
Slide 8
PASSENGER SIGNS Panel ATTND CALL Button: Pressing this button
sounds a chime in passenger cabin and illuminates the GREEN light
on the Flt Attnd rainbow FSTN SEAT BELTS Toggle Switch: ON
Illuminates the FASTEN SEAT 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 chime in the cabin NO SMKG Toggle
Switch: ON Illuminates the NO SMOKING signs. Turning the switch ON
a single low tone chime in the cabin. OFF - Turns off the NO
SMOKING signs. Turning the switch OFF sounds a single low chime in
the cabin. NOTE: The both signs (NO SMKG and FSTN BELTS) will
automatically illuminate when the Oxygen Masks are commanded to
deploy. NO SMKG STERILE Toggle Switch: ON Illuminates the AMBER
sterile light on the Flt Attnd rainbow. Turning the switch ON
sounds a single high tone chime in the cabin OFF Turns off the
AMBER sterile light on the Flt Attnd rainbow. 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. 1 - How
long will the batteries supply emergency power? (ELPUs)
Approximately 10 minutes.
Slide 9
FIRE EXTINGUISHER Panel #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 deacelerates. ROTATE (left (A) or right (B)) Discharges
the associated fire extinguisher bottle into the associated engine.
CARGO SMOKE FWD and AFT Buttons (GUARDED): Momentary action
pushbutton. Illuminates when the high rate bottle is armed. 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. Fire
Detection System TEST Button Test the engines and APU fire
detection systems, and the FWD / AFT cargo compartment smoke
detection system. Check there no EICAS MSGs before do the test:
FIRE DET FAIL, FIREX FAIL, FIREX ARM, BTL DISCH. A valid test is
indicated by: 6 overhead panel lights, 5 EICAS messages and 4
lights (MASTER WARNING and ITT FIRE icon on engine 1 and 2.
Slide 10
What indications are you looking for when you press & hold
the Fire Detection TEST? Aural Warnings: Continuous bell Triple
chime (silence by pressing either master Warn Light) Overhead Panel
Engine1 Fire Extinguishing handle, Engine 2 Fire Extinguishing
handle, Lights: (6)Fire Extinguisher Cargo Smoke FWD pushbutton,
Fire Extinguisher Cargo Smoke AFT pushbutton, Fire Extinguisher APU
pushbutton, APU Control EMER STOP pushbutton (upper half) EICAS
MESSAGE: ENG 1 FIRE, (5)ENG 2 FIRE, APU FIRE, CARGO FWD SMOKE,
CARGO AFT SMOKE. Warning lights:MASTER Warning (Flashing) (2), (4)
Left and right FIRE warning icon on ITT EICAS indicators.
Slide 11
APU CONTROL Panel EMER STOP Button: PUSH IN Closes the APU fuel
shutoff valve, shutting down the APU without 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 shutoff valve open. MASTER Knob: OFF Normal position
when the APU is not running. ON - Normal position when the APU is
running. START (Momentary action) Iniciates the APU starts cycle.
NOTES: 1 Moving the 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 rotatory
knob is positioned to OFF. If the APU generator is the only source
of AC power during the cool down, the APU electrical power will
still be available during the one minute cool down period. If there
is other source of AC power on the aircraft when the MASTER
rotatory knob is moved to OFF, then APU electrical power is removed
right away. 2 During any portion of the one minute cool down, the
MASTER rotatory knob can be moved from OFF back to ON and the APU
will continue running. LIMITATION !!!
Slide 12
WINDSHIELD WIPER Panel #1 and #2 WINDSHIELD WIPER Control:
TIMER Provides eight-second intermittent operation. OFF Stops
windshield wipers on the stowed position. LOW Windshield wipers
operate at low speed. HI Windshield wipers operate at high speed.
NOTE if both windshield wiper knobs are selected to LOW/HI they
will be sync to the captains (#1) controller. Windshield wipers
will not operates on a dry windshield. 1 - What is the maximum
windshield operation speed if the windshield is failed in the park
position? 253 Kt. 2 - What happens when you select the WINDSHIELD
WIPER selector knob to timer? The windshield wipers operate on a 8
seconds intermittent operation. Low (80 cycles per min) High (120
cycles per min). LIMITATION !!!
Slide 13
EXTERNAL LIGHT Panel NAV, STROBE and RED BCN Switches: Turns
ON/OFF the associates light. INSP Light Switch : Turns ON/OFF the
inspection lights. LOGO Light Switch : Turns ON/OFF the logo
lights. TAXI Light Switches: Turns ON/OFF the taxi lights. LANDING
Light Switches: Turns ON/OFF the associated landing lights RT I-OPS
20/09
Slide 14
HYDRAULIC System Panel PTU Switch: OFF Turns the PTU OFF. AUTO
During takeoff or landing, with the flaps not at zero, the PTU will
active with a failure of ENG 2 Engine Driven Pump to provide normal
LDG GEAR extension and retraction. ON The PTU operates
continuously. SYS 1 and SYS 2 ENG PUMP SHUTOFF Buttons (GUARDED):
Momentary action pushbuttons PUSHED IN Closes the Hydraulic shutoff
valve (SOV), isolating the respective EDP from the associated
hydraulic system. PUSHED OUT - Normal position. Hydraulic SOV open.
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 0; and the
thrust levers are advanced beyond 60 degrees of TLA, or the ground
speed is greater than 50 Kts. Additionally, the SYS 2 HYD PUMP will
run automatically for single engine taxi when ENG 1 has been
started and the EMER/PRKG BRAKE Handle has been released. In Flight
SYS 1 and SYS 2 will operate automatically with the failure of its
EDP, or when flaps are not at zero. ON Operates the electrical pump
continuously. SYS 3 ELEC PUMP A Selector Knob: OFF Turns the
electrical pump OFF. ON Operates the electrical pump continuously.
SYS 3 ELEC PUMP B Selector Knob: OFF Turns the electrical pump OFF.
AUTO In flight the pump will turn ON when SYS 3A ELEC PUMPfails. ON
Operates the SYS 3 B pump continuously.
Slide 15
1- What happens when you push the SYS 1 and SYS 2 ENGINE PUMP
SHUTOFF guarded buttons? Closes the hydraulic SOV, isolating the
respective engine driven pump (EDP). 2 - What is the Purpose of the
PTU? The PTU uses system 1 hydraulic pressure and the system 2
hydraulic fluid to provide additional power to retract or extend
the Landing Gear. 3 - When will the PTU operate automatically? With
the PTU control knob in auto, and the flaps not set to zero if the
Engine or EDP 2 fails. 4 - What is the purpose of ELEC PUMP A and
ELEC PUMP B? Elec pump A is used to pressurize Hydraulic 3 System A
( primary source). AC ESS BUS powers it. Elec pump B is a backup of
the electrical pump A. AC BUS 2 powers it. 5 - What happens when
the SYS 1(2) ELEC Pump selector knob is in AUTO? Activates the
electric pump whenever the EDP pump fails or when the flaps are
selected to any position greater than zero. For takeoffs and
landings the pumps are automatically activated when the flaps are
not to zero and one of the following conditions occurs: Thrust
Levers set to takeoff thrust; Weight on Wheels switch activated in
flight; Groundspeed is greater than 50 kt. 6 - What causes SYS 2
ELEC PUMP to operate during single engine taxi? On the ground,
after starting engine number 1, releasing the parking brake will
automatically activate electric pump 2 to allow single engine taxi.
7 - What is the primary hydraulic source for hydraulic system 3?
SYS 3 ELEC PUMP A. 8 - What is the purpose of SYS 3 ELEC PUMP B and
what happens when the selector switch is in AUTO? Backs up SYS 3
ELEC PUMP A. In AUTO, SYS ELEC PUMP B will come on when SYS ELEC
PUMP A fails. 9 - How would you be alerted to a hydraulic low
quantity or over temperature? On the MFD synoptic page and EICAS
display.
Slide 16
PRESSURIZATION Panel DUMP Button (GUARDED): When pushed in, a
white striped bar wil 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 12.400 ft at 2.000 FPM. once the cabin has
been dumped to 12.400 ft natural leak will raise the cabin higher.
If the cabin dump has been commenced, it can be cancelled by
reselecting the button to its normal (OUT) position. Pressurization
MODE Selector Knob: MAN Allows manual control of the Outflow Valve.
LFE CTRL Allows manual input of landing field elevation. This
funtion is usedwhen the FMS is inoperative, or when landing at na
airport is not in the FMS database. Other automatic funtions of the
pressurization system remain opertive. LFE Knob: Manual input of
the LFE is only possible when the pressurization MODE Knob is
selected to LFE. DOWN Decreases of the LFE in 100 increments. If
held longer than 5 seconds, the LFE will increase in 500
increments. STOP (spring loaded) Normal operation position UP
Raises the LFE in 100 increments. If held longer than 5 seconds the
LFE wil increase in 500 increments CAB ALT Selector Knob: Rotary
Knob is only active when the pressurization MODE knob is selected
to MANUAL.. DOWN Manually closes the Outflow valve. STOP (spring
loaded) Normal operation position UP Manually opens the Outflow
valve. 1 -What does the cyan M indicated on the EICAS? A cyan M in
front of the altitude readout indicates manual input of the landing
field elevation. 2 - How can you determine the position of the
outflow valve? There is a pointer on the outflow valve position
indicator on the environmental synoptic page. 3 - WHAT ARE THE
MEMORY ITEMS FOR CABIN ALTITUDE HI? OXYGEN MASKSON, 100% CREW
COMMUNICATIONESTABLISH LIMITATION !!!
Slide 17
ICE PROTECTION Panel WINDSHIELD HEATING BUTTON 1 and 2: PUSH IN
Allows automatic operation of the associated windshiel heating
system. PUSH OUT Deactivates the associated windshield heating
system. Notes: On the ground with one sorce of AC power, power to
both windshield heaters is shed. In flight with one souce of AC
power, power to the F/Os windshield is shed. In case of failure of
the Captains windshield power will be supplied to the F/Os
windshield. 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 TEST Knob:
(Maintenance procedure) ENG Provides test for the engine anti-ice
sys. OFF Spring-loaded position. WING Provides a test for the wing
anti-ice sys. ENGINE ICE PROTECTION Button (1 and 2): 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. ICE PROTECTION MODE Selector Knob: AUTO
Allows automatic operarion of the wing and engine anti-ice systems.
ON Overrides the system logic in flight, activating the anti-ice
system regardless of ice condition. 1 - When the ice detectors
automatically active the engine and wing. How long will the ice
detectors remain activated? For 5 minutes after the detector is no
longer sensing an icing condition. 2 - How many Ice Detectors is
the airplane equipped with? 2 (Two) 3 - What would happen with the
failure of one Ice Detector? If the remaining detector senses an
icing condition, the system automatically activates the ENGINE and
WING anti-ice system. 4 - What happens in the event of a bleed air
source failure? The system automatically opens the cross feed valve
supplying airflow from one engine bleed to the opposite wing
anti-ice. LIMITATION !!!
Slide 18
Slide 19
AIRCOND/PNEUMATIC Panel RECIRC Button: PUSH IN Allows the
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. PAX CABIN Temperature Control Knob: Controls passenger cabin
temperature according to the knob position. Rotating the knob to
the ATTND position allows cabin temperature control via flight
attendant control panel. CKPT Temperature Control Knob: Controls
cockpit temperature according to the knob position. PACK 1 and PACK
2 Buttons: PUSH IN Allows for automatic operation by AMS. This
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, smoke is detected in the recirculation bay,
the thrust levers are set to MAX, or during take off with REF ECS
OFF and APU BLEED unavailable. XBLEED Button: PUSH IN Allows the
AMS to control automatic operation of the crossbleed valve. PUSH
OUT Manually closes the crossbleed valve. APU BLEED Button: 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 APU BLEED Button. BLEED 1 and BLEED 2 Buttons:
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 bleed leak
will cause the illumination of an AMBER striped bar in the upper
half of the associated engine bleed button. 1- When is the DUMP
pushbutton used for? The DUMP function is used for emergency
evacuation, smoke removel, and fast cabin depressurization.
Pneumatic bleed source priority is: on side bleed, off side bleed
and APU bleed. When the engine and APU bleed are available
simultaneously, the AMS gives priority to APU to supply bleed
requirements when the following conditions are simultaneously met:
the airplane is on the ground, the opposite engine bleed pressure
is below the minimum for engine start, the ground speed is below 50
Kts and the crossbleed valve is operating normally. 2 - Can the APU
bleed be used for the anti ice system? No. LIMITATION !!!
Slide 20
PASSENGER OXYGEN Panel 3 - What protects the bleed system from
an overheat condition? The overheat detection system. 4 - When is
the Emergency Ram Air Valve commanded to open? Anytime the airplane
is in flight and both air conditioning packs commanded OFF or
failed OFF and the airplane altitude is less than 25000 feet. 5
-How many channels does the Cabin Pressure Controller have? The CPC
has 2 fully independent automatic channel that alternate after each
flight. 6 - What prevents the cabin from negative pressure? The
negative pressure relief valve NPRV. Open with -0.5 PSI
overpressure 7 - Does the positive pressure relief valve require
electrical power to operate? No. 8 - What happens to the Landing
Field Elevation (LFE) in the ABORT mode? During the ABORT mode the
cabin pressure is scheduled back to the takeoff altitude. Is not
possible if: Cruise mode has already entered; airplane is above
10000ft or airplane is 5000ft above takeoff field MASKS DEPLOY
Knob: OFF Disables automatic deployment of passenger oxygen masks.
AUTO Enables automatic deployment of passenger oxygen masks when
cabin altitude is above 14.000 ft. OVRD Deploys the passenger
oxygen masks regardless of cabin altitude. Note: The NO SMKG and
FSTN BELTS will automatically illuminates when the oxygen masks are
command to deploy. MASKS DEPLOYED Indicator: An ON light
illuminates, indicating that the passenger and flight attendant
oxygen masks have been commanded deploy. 1 - Where would you find
the oxygen system parameters and indication? On the MFD synoptic
pages and the EICAS displays.
Slide 21
Main Instrument Panel Reversionary Panel Primary Flight Display
(PFD) Multi Function Display (MFD) Glareshield Lights Press To Talk
(PTT) Master Warning/ Caution Guidance Panel Integrated Electronic
Standby System (IESS) Autobrake Engine Indication and Crew Alerting
System Display (EICAS) Clock / Chronometer Ground Proximity Terrain
Inhibit Emergency Parking Brake ELT Landing Gear Controls Ground
Proximity / Glideslope Landing Gear Warning Inhibition Button
Slide 22
GP AFCS Controls FD Button: AP Button: Commands autopilot
engagement or disengagement Note: The AP disconnect warning can
olny be cancelled by pushing the yoke AP/TRIM DISC Button AT
Button: GROUND - Arms the autothrottle system. IN FLIGHT Engages or
disengages the AT system. Note: The AT disconnect warning can only
be cancelled by pushing one of the thrust lever mounted AT DISC
buttons. YD Button: Engages or disengages the Yaw Damper/ Turn
Coordination funtion. YD defauts ON at system power up. Tured ON
when the AP is engaged. SRC Button: Selects the CPT or FO AFCS side
as data source. A GREEN arrowhead on the FMA indicates the selected
side.
Slide 23
Vertical Guidance Controls VS Button : Activates or deactivates
the VS mode. VS Thumb Wheel: Manually selects the desired vertical
speed if VS is the active vertical mode. VNAV Button: Activates or
deactivates vertical navegation. VNAV vertical modes will appear
magenta in the FMA. FLCH Button: Initiate a climb or descent basead
on the current FL (altitude) X altitude selected. With AT engaged:
CLB in thrust levers in TOGA, Descent T.L in IDDLE. Altitudes CHG
> 2000 modulates between them. TRS will always be CLB. In FLCH
pitch is commanded to mantain airspeed. ALT Button: Activates or
deactivates the altitude HOLD funtion. FPA SEL Knob: Manually
selects the desired Flight Path Angle if FPA is the active vertical
mode. IF FPA is not the active mode and FPR is selected on the
Display Control Panel, this knob adjusts the position of the flight
path reference line. This fllight path angle is limited 9,9 degrees
nose up or down. ALT SEL KNOB: Selects the desired altitude in 100
increments. Clockwise roation increases the altitude target.
Counterclockwise decreases the altitude target. Note: Pressing the
center button on the knob will active or deactive the metric
presentation of current altitude on the PDF. FPA Button: Activates
or deactivates the Flight Path Angle mode. This is the BASIC
VERTICAL MODE.
Slide 24
Lateral Guidance Controls SPEED and MODE Controls SPEED
Selector Knob: OUTER FMS : The desired speed is controlled by the
FMS. Changes can be entered through the MCDU. FMS speed is
displayed in MAGENTAon the PFD. MAN: The desired speed is
controlled manually, displayed in CYAN on the PFD. INNER Manually
selects the desired airspeed. Manual speeds are displayed in CYAN
on the PFD. PUSH IAS - MACH: Toggles the speed selected on the PFD
between IAS and MaACH. HDG Button: Selects or deselects HDG as the
lateral navegation mode. HDG SEL Knob: Manually selects the desired
heading. Pressing the center of the knob will center the heading
bug to the current heading. NAV Button: Selects or deselects
VOR/LOC or LNAV as the lateral navigation mode. BANK Button:
Selects or deselects the bank limiting funtion of the AFCS. A withe
arc will appear on the bank indicator of the PFD when bank limiting
is engaged. Bank limiting is available in HDG mode only. APP
Button: Activates or deactivates the appraoch mode of the AFCS for
intercept an ILS or BC. For an ILS, the autopilot approach status
annunciator displays the following: APPR 2 CAT II ILS Capable; APPR
1 CAT I ILS Capable; APPR 1 ONLY System logicis requesting CAT II
guidance but only CAT I is capable.
Slide 25
Display Controller Panel MINIMUMS Knob: OUTER - Sets the
appoach minimuns for all nonprecision and precision approaches. RA
Allows for autocallouts based on the RADAR altimeter. This position
is used only for CAT II ILS approaches. BARO Allows for
autocallouts based on the barometric altimeter. This position is
used for all CAT I ILS and nonprecision approaches. INNER Adjusts
up or down the selected approach minimuns. The value will be
displayed on the PFD. Rotation counterclockwise beyond 0 will turn
the display and auto callouts OFF. V/L Button: Selects VOR or LOC
as the navigation source, and displays a GREEN needle on the PFD
HSI. The needle can be toggled between ON SIDE and CROSS SIDE
navigation information. FMS Button: Selects FMS as the navigation
source, and displays a MAGENTA needle on the PFD HSI. Can be toggle
between side and cross side navigation information. WX Button: When
the HSI button has been toggled to display arc with map on th PFD,
the WX button turn ON/OFF the display of WX RADAR information on
the PFD map. WX RADAR information can be only displayed on the PFD
map when MAGENTAneedles are selected. FPR Button: Selects or
deselects the display of a cyan flight path reference line on the
PFD. The FPA SEL Knob can be rotated to change the value of this
line +/- 9,9 degrees HSI Button: Toggles the HSI view on the PFD
between full compass rose, arc and arc with map. BARO SET Knob:
INNER - Sets barometric altimeter correction. Pushing this control
Knob sets barometric correction to standard. OUTER IN sets
altimeter in inches of mercury. HPA Sets the altitude in
Hectopascals. BRG Buttons: CIRCLE Displays #1 RMI bearing pointer
information on PFD. (VOR 1, FMS 1 or OFF). DIAMOND Displays #2 RMI
bearing pointer information on PFD. (VOR 2, FMS 2 or OFF). PREV
Button: Selects or deselects the display of lateral and vertical
deviation information from the tuned VOR/ILS/LOC frequency while
FMS is the active navigation source. A blue needle depicts the PREV
information. Toggling the PREV button alternates the display of on
side or cross side navigation information. For a LOC/BC or ILS, if
APPR mode is armed, the previewed navigation source will become the
primary navigation source when cacptured. The PREV needle wont
change to amber when cross side information is displayed.
Slide 26
Glareshield Lights Control Panel Turns ON/OFF and sets the
brightness of the flood/storm panel lighting. Provides maximum
brightness for storm conditions at BRT position.
Slide 27
REVERSIONARY Panel IRS Button: Momentary action pushbutton;
reverts the IRS source. When pushed in, a withe stripe illuminates
on the button. Notes: IRS source flag is displayed on the PFD. IRS
reversion must be performed manually. ADS Button: Momentary action
pushbutton; reverts the ADS source. When pushed in, a withe stripe
illuminates on the button. Notes: ADS source flag is displayed on
the PDF. ADS reversion is automatic. DISPLAYS Knob: PFD - Forces
the associated MFD to displays as PFD. AUTO Allows automatic
reversion of the MFD in case of display failure. MFD Forces the
associated MFD to displays as an MFD. EICAS Forces the associated
MFD to displays as an EICAS. 1 - What happens with the DISPLAYS
selector in AUTO? Automatically reverts the MFD 2 or 4 in case of
display failure. (AOM 14-01-3) EDS AUTO REVERSION LOGIC:
Slide 28
Primary Flight Display (PFD) AVIATE: AUTOPILOT APPROACH STATUS
ANNUNCIATOR FLIGHT MODE ANNUNCIATOR ATTITUDE AND SIDESLIP ALTITUDE
AIRSPEED MACH AIRSPEED TREND VECTOR VERTICAL SPEED FLIGHT PATH
ANGLE FLIGHT PATH VECTOR TOTAL ENERGY FLIGHT DIRECTOR TCAS
RESOLUTION ADVISORY WINDSHEAR RADIO ALTIMETER NAVIGATE AND
COMMUNICATE: HEADING WEATHER RADAR ILS/VOR/DME RADIO COMMUNICATIO
TUNNING RADIO NAVIGATION TUNNING FMS ANNUNCIATION/INDICATION WIND
ELAPSE TIME The PFD displays information such as airspeed
indicator, altitude indicator, ADI, HSI, vertical speed indicator,
radio aids, autopilot, flight director and radio altitude data. In
the event of display failure, information will be automatically
presented in the PFD. The display controller portion of the
guidance panel allows the selection of PFD HSI formats, navigation
sources, weather display and bearing pointer selection.
Slide 29
Multi Function Display (MFD) NAVIGATE: MAP PLAN SYSTEM SYNOPTIC
PAGES TCAS WEATHER RADAR EGPWS (TERRAIN) NAVIGATE (VNAV): TCAS ZOOM
WEATHER RADAR CONTROLLER TCAS CONTROLLER The MFD presents map and
plan navigation formats and various systems synoptic formats
selected by the flight crew. The MFD provides redundancy to display
both the PFD and EICAS formats based upon reversion. It also has
the ability to display maintenance information. The MFD consists of
menu softkeys, on the top and bottom of the screen, which are used
to select formats and control various systems.
Slide 30
Integrated Electronic Standby System (IESS) Brightness
Adjustment Buttons ILS Button: Selects or deselects the display of
ILS 1 LOC and GS deviation indications on the IESS. ILS 1 will be
annunciated in the upper left corner of the IESS. Ins case of
failure, a red cross replaces the annunciation. STD Button: Sets
the barometric pressure to standard atmospheric pressure Brightness
cell: Automatically adjusts the instrument brightness according to
the ambient lighting. BARO Knob: Allows manual setting of the
altimeter. CAGE Button Resets altitude to zero, eliminating
accumulated drift when the button is pressed for more than 2
seconds. Not operational during the inicialization mode and must be
used with wing leveled on stabilized flight conditions. When
pressed, an AMBER CAGE flag is displayed on the upper right corner
of the IESS. 1 -What does the IESS do? Displays Attitude (pitch and
roll), altitude and indicated airspeed. 2 - When is the IESS
powered? When batteries are switched to AUTO. 3 - How is the IESS
powered in an emergency? The EISS is powered by the RAT or by the
batteries.
Slide 31
AUTOBRAKE Panel There are 2 modes of autobrake control:
1.LANDING MODE (LO, MED or HI) 2.REGECTED TAKEOFF MODE (RTO)
LIMITATION !!!
Slide 32
GND PROX TERR INHIB Pushbutton / PRKGBRAKE Light Clock /
Chronometer Display When pressed, inhibtis EGPWS and thus avoid
unwanted terrain alerts in airports not covered by EGPWS database
The word ON illuminates when the EMERG/PRKGBRAKE is actuated.
Illumination of the light indicates that sufficient hydraulic
pressure is available to main brake pressure CHR Button:
starts/stops the chronometer. GPS/INT/SET Button: GPS synchronizes
with UTC and DATE from GPS. INT displays information from the
internal clock. SET sets the clock modes. ELAPSED TIME SELECTOR:
AUTO (sprieng loaded neutral) automatically starts the chronometer
on liftoff. RST resets the elapsed time if WOW is present.
Clock/Chronometer Display: If no GPS signal is detected, the clock
will display dashes and only the positions INT and SET will be
avbl. The CHR display is blanked in the non-operating mode. RST
Button DATA/SET Button: Allows time setting when the GPS/INT/SET
selector is in SET position. Repeated pressing of the SET button
causes the selector to cycle between minutes, hour, year, month and
day. The desired digits flash and the setting is obteined by
rotating the DATA/SET button. Allows the date to be displayed on
the associated indicator when the GPS/INT/SET selector is set to
GPS or INT. 1 - What is indicated when the clock displays dashes
(----)? No GPS signal is detected.
Slide 33
Engine Indication and Crew Alerting System Display (EICAS) The
EICAS displays engine and system parameters such as flap, gear,
spoiler and trim positions, total fuel quantity, APU and
environmental information. The EICAS also displays warning,
caution, advisory and status messages. In case of failure in the
EICAS display, its information may be presented in the MFD by
appropriately setting the reversionary panel. An automatic mode de-
cluters the EICAS after takeoff. (occurs 30 seconds after landing
gear and flap/slat retraction. The following items are de-
cluttered from EICAS: Oil Pressure; Oil Temperarure; Engine
Vibration; Flap position; Speed brake position; Pitch trim green
band; Slat position; Landing gear position (if Autobrakes are OFF).
MANEGEMENT ENGINE GEAR FLAPS TRIM IN normal conditions, de-clutter
wil be desabled when one of the above parameters is no longer in a
normal indicating range, not stowed, or not up and loked.
Additionally, arming the Autobrake for landing will desable the
de-clutter funtion of the EICAS.
Slide 34
Landing Gear Panel ELT Panel ON Activates the ELT. ARM - Arms
the ELT. LANDING GEAR Lever: UP Retracts the landing gear. Down
Extends the landing gear. DN LOCK REL Button: Mechanically releases
the landing gear lever lock. 1 - What does a red icon indicate on
the landing gear position indicator? A discrepancy between the
landing gear lever position, and the respective landing gear
position. 2 - What are the 3 landing gear extension modes? Normal
extension (electrically-controlled by the PSEM). Electrical
override extension (electrically-controlled by the override
switch). Alternate gear extension (mechanically-controlled, by the
freefall system)
Slide 35
GND PROX GS INHIBIT and WRN INHIBIT Panel MASTER CAUT and WAR
Pushbuttons Momentary pushbutton annunciator to manually cancels GS
alerts. Illuminates when pressed any time below 2000 ft RADAR
altitude and will automatically reset (light off) by climbing above
2000 ft RADAR or descending below 30 ft RADAR altitude. Pressing
the button will inhibit the landing gear warning in the event of a
dual radio altimeter failure. When pressed a white bar will
illuminate inside the button and will extingish allowing a new
warning when the Thrust Levers are advanced. IF flap 5 or FULL is
selected with the gear up the warning cannot be cancelled. A RED
light blinks inside the button when a new warning message is
displayed on the EICAS. Pressing the button extinguishes the light
and silences the associated aural alert (triple chime). An AMBER
light blinks inside the button when a new caution message is
displayes on the EICAS. Pressing the button extinguishes the light
and silences the associated aural alert (single chime).
Slide 36
Control Pedestal Multifuntion Control Display Unit (MCDU)
Engine Control Panel EICAS Full Panel Takeoff Config Check Button
Flight Control Mode / Stall Warning Panels Cursor Control Device
(CCD) Speedbrake Lever Thrust Control Emergency / Parking Brake
Handle Trim Panel RAT Manual Deploy Flap Override Switch Flap /
Slat Selector Lever Reinforced Cockpit Door Passenger Address PTT
Aileron Disconnect Handle Impressora Elevator Disconnect IFE / CSS
Power Panel
Slide 37
FLIGHT CONTROLS MODE and STALL WARNING Panel POWERPLANT and
IGNITION Panel FLIGHT CONTROLS MODE Buttons (GUARDED): PUSH IN
Selects DIRECT MODE for the associated flight control. A white bar
will illuminate in the push button. PUSH OUT Returns the associated
flight control to NORMAL MODE. SHAKER CUTOUT Button: PUSH IN Cuts
out the associated yoke shaker channel. PUSH OUT Allows normal
operation of the shaker. START / STOP Selector Knob: STOP Commands
the FADEC to shut down the engine, provided the associated thrust
lever is in IDLE Position. RUN Normal condition for engine
operation. START (momentary action) Iniciates the start sequence.
IGNITION Selector Knob : OFF Deactivates the ignition system on the
ground. The FADEC disregars the OFF position in flight. AUTO FADEC
automatically controls the ignition system, depending on engine
requirements. OVRD Directs FADEC to continuously activate both
igniters. LIMITATION!!! 1 - What happens when the stick shaker is
activated? Control column authority is limited in the nose up
direction. 2 -How would you be alerted to an AOA limit failure? An
EICAS message.
Slide 38
Multifunction Control Display Unit (MCDU) 1 1 The MCDU allows
the FMS control, radio tuning, PFD radio tuning, display setup,
manual engine rating selection, engine takeoff data set and
avionics display setup and test. Line Select Keys (LSK) : Data is
selectedto a line from the scratchpad or vice- versa. On the radio
pages only, if a single white triangle is displayed, a sub-menu
will be available to view when the LSK is pushed twice. The first
push will bring the cursor box to the LSK selected, and the second
push will open the sub-menu. SCRATCHPAD: The working area, located
on the button line of the display. The pilot can enter data and /
or verify data before line selecting the data into the proper
position. Data is retained on the scratchpad throughout all modes
and provides advisory and alerting messages. BRT / DIM Switch
Tuning Knob PERF Displays the performance page. NAV Displays the
navigation page. FPL Displays the flight plan page. PROG Displays
the progress page. RTE Displays the route page. CB Displays the
circuit breaker page. MENU Displays the menu page. DLK ACARS
functions TRS Thrust rating select. RADIO Displays the radio page.
LIMITATION!!!
Slide 39
T/O CONFIG Button and EICAS FULL Button T/O CONFIG Button:
Checks the Takeoff configuration : EMERG/PRKG BRAKE OFF, takeoff
flaps set, spoilers retracted and pitch trim in the green band.
EICAS FULL Button: 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
landing gear snd slat/plap retraction if all parameters are
displaying normal indications. The following items are de-cluttered
from the EICAS: Oil temperature Oil pressure Engine vibration Flap
position Speed brake position Pitch trim green band Slat position
Landing gear position (if AUTOBRAKES are OFF) 1 -What is the
indication of a suitable takeoff configuration? A voice message
TAKE OFF OK is generated. 2 - What happens if the airplane is not
set to the take off configuration? An aural warning is generated
that will refer to the associated take off configuration
deviation.
Slide 40
Cursor Control Device (CCD) Tuning Knob; Outer and Inner knobs
select values or modes in the data field enclosed by the cursor.
CPT Side EICAS MFD PFD Touch Pad Enter Key RAT MANUAL DEPLOY Handle
Ram Air Turbine Deployment Handle: Manually deploys the ram air
turbine. GND PROX FLAP OVRD Switch (GUARDED) EMERG/PARKN Brake
Handle Actuates the emrgency / parking brake. The handle will lock
when pulled up to the fully actuated position. To release the
handle from the fully actuated position, the button must be
pressed. Note: If an GPU were connected to the airplane, when
EMERG/PRKN BRAKE become release a message will be displayed on the
EICAS GPU CONNECTED. Inhibits triggering of flap alerts in case of
landings where flap configuration is other than 5 or FULL.
Slide 41
Speedbrake Lever 1 - When does full Multi-function spoiler
extension occur? Weight on Wheel on ground, Wheel speed is above 45
knots on airspeed is above 60 kt and Thrust Lever Angle (TLA) below
26 degrees. 2 - What will happen if the speed brakes are extended
during approach? The speed brakes will automatically retract upon
selection of Flap/Slat 2, speed less than 180 kt or TLA beyond 70.
3 - When will the speed brakes automatically retract during a
go-around maneuver? When the Thrust Lever Angle (TLA) is advanced
beyond 70 degrees. 4 - Are speed brakes available in the direct
mode? No. 5 - What indication on the EICAS would indicate the speed
brakes are open? A white SPDBRK annunciation. In flight,
symmetrically deploys the multi-function spoilers in proportion to
the speedbrake lever position. The speedbrakes will automatically
retract when the thrust lever angle exceeds 60 degrees, greater
than FLAP 1 is selected, or the speed drops below 180 KIAS. Notes:
The speedbrake lever does not move for autoretraction, or for
ground spoiler deployment. The speedbrake lever is inhibited on the
ground.
Slide 42
Thrust Levers MAX Provides the maximum thrust avbl. TOGA
Selects takeoff, go around and maximum continuos thrust ratings.
IDLE Selects idle thrust settings. MIN REV Provides minimum reverse
thrust. MAX REV Provides maximum reverse thrust. The lever must be
pulled against a spring to achieve the MAX REV position. If it is
released goes back to MIN REV position. Thrust Reverser Trigger:
Pulling the thrust reverser trigger allows movement of the thrust
levers aft of the IDLE stop (on the ground only). AT DISC Button:
Disconnects the autothrottles and cancels the AT aural alert. 1 -
How is the FADEC powered? The FADEC is primarily powered by the
Permanent Magnet Alternator (PMA) above approximately 50% N2. Below
this value or in case the PMA becomes inoperative, the airplanes
electrical system provides the required backup power. 2 - How many
channels does the FADEC computer have? 2 identical isolated
channels. During operation with 2 capable FADEC channel, the
software logic will alternate the channel in control of each eng
start. 3 - What controls engine starting and provides hung star,
hot start and no light off protection? The FADEC. 4 - How is the
ATTCS system controlled? The FADEC. 5 - If the ATTCS is selected
off for take-off, will it be available for go-around? Yes, it will
be armed automatically during the go-around mode. 6 - What is a
Flexible Thrust take-off? A reduced take-off thrust based on an
assumed temperature. 7 - How is engine thrust ratings controlled?
By the FADEC. 8 -How long is the Go Around mode limited to in the
go-around phase? 5 minutes. 9 - The FADEC has four idle modes, what
are they? Flight idle, Approach idle (Weight off wheels, flap 1 or
greater or landing gear down), Final Approach idle (at 1200ft and
considers anti-ice off regardless of anti- ice system) and Ground
idle. 10 - Where would you set the TO thrust rate mode and TO
temperature? In the T/O DATASET MENU key, on the MCDU. 11 - The
application of maximum thrust is not permitted below what airspeed?
60 Kts. LIMITATION!!!
Slide 43
Audio Control Panel (ACP)
Slide 44
SLAT / FLAP Lever Selects slat / flap position. The lever must
be unlaached by and lifting the trigger below the head.Intermediate
position are not enable. Position 4 is gated. Allowable takeoff
position are 1, 2, 3 or 4. Normal landing positions are 5 or FULL
LIMITATION !!! TRIM Panel Pitch trim priority is: backup trim, CPT
trim, FO trim and AP trim. To prevent trim runaway situations all
trim actuation is limited to 3 seconds of movement. The switch 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. ROLL trim Switch: Actuates the roll trim L or R. PITCH
BACKUP SW: Actuates the pitch trim through the backup channel.
Operation of this SW when the AP is engaged causes the AP to
desengage. YAW Trim Switch: Actuates the yaw trim to L or R. SYS 1
(2) CUTOUT Switch (GUARDED): PUSH IN Disables pitch trim channel 1
(2). PUSH OUT Enables pitch trim channel 1 (2). 1 - How do you
accomplish the trim Check? Push and hold for 3 seconds to verify
automatic stop.
Slide 45
COCKPIT DOOR CONTROL Panel LOCK Pushbutton (GUARDED): Locks and
unlocks the door. A white bar in the switch illuminates when unlock
button is selected (push in). Deactivates the inhibition control.
Resets the buzzer alarm and EMERG CALL commanded. Resets the GREEN
LED on the flight attnd access panel. TEST Button: Continually
tests the buzzer while the test button is pressed, regardless of
audio selection. UNLOCKED Indicator: Illuminates ON when the door
is unlocked. When access is requested an intermittent chime will
sound in the cockpit and the ON light will flashe on and off. INHIB
Pushbutton (MOMENTARY ACTION): Pushing this button will lock the
door for 500 seconds if emergency access is requested. When pushed
a white bar will illuminate in the button. If emergency access is
requested and INHIB is not selected whitin 30 seconds the door will
unlock. PA Button: Allows voice communications to the customers
regardless of the MIC selection on the ACP.
Slide 46
IFE / CCS POWER Panel CABIN IFE Button (GUARDED): Controls the
power supply to the Live TV system and the XM Satellite Digital
Radio. A stiped bar illuminates in the button when selected OFF.
CCS Button (GUARDED): Controls power to the Cabin Surveillance
System. A striped bar illuminates in the button when selected OFF.
IFE RACK Button (GUARDED): Controls power to the Live TV System,
the CCS, XM Satellite Radio System and Wireless Aircraft Data Link
(WADL). Controls power to the PA buffer, rack fan and flow switch.
Power to smoke detection and ventilation system is not turned off
by pressing this switch. A striped bar illuminates in the button
when selected OFF. PRINTER
Slide 47
Disconnect Handles 1 ELEVATOR DISCONNECT Handle: PULL
Disconnects the elevator control system. Each pilot will control
their on-side elevator. The system can not be reset in flight.
Disconnection can be confirmed by a ELEVATOR DISC EICAS message. 2
AILERON DISCONNECT Handle: PULL Disconnects the aileron control
system. The CPT will control his/her on-side aileron, MFS panel
5L/R with artificial feel. The FO will control his/her on-side
aileron, MFS 4L/R with artificial feel. MFS panel 3L/R is locked
out for both pilots. The system can not be reset in flight.
Disconnection can be confirmed by a AILERON DISC EICAS message.
Alternate Gear Extension Compartment
Slide 48
YOKE (Control Wheel) CONTROL WHEEL COMMUNICATION SWITCH: PTT
(momentary) Allows VHF transmissions as well as PA announcements.
HOT Allows INPH communications over the HOT mic. OFF Allows only
audio reception. CHRONO: It has three functions: START-STOP-RESET.
The timer appears on the upper right corner of the PFD HSI. Tiller
TOUCH CONTROL STEERING BUTTON (TCS): Allows
adjustment/syncrhronization of certain FGCS modes, and manual
maneuvering of the aircraft if the AP is engaged. Pressing and hold
the button causes: (If AP is engaged) disengagement of the AP
servos, allowing manual aircraft maneuvering, Synchronization of
the FD guidance cue to the FPV. Release of the button causes: AP
servos to reengage, if AP was engaged prior to TCS selection, FD
cues to resume movement to guide toward active lateral and vertical
modes, FGCS lateral mode: control returns to previosly selected
lateral mode, FGCS vertical mode. VS or FPA synchronize with
(VS/FPA) exiting button release. ALT synchronizes to the altitude
exiting button release. FLCH or GS control returns to that mode.
LIMITATION !!! Trigger behind the yoke: