CRJ Systems > Overhead panel > Flashcards

Overhead panel Flashcards

(71 cards)

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1
Q

Electric- DC Service Switch

A

Used to connect the DC service bus to the
APU battery direct bus.

Service Lights Galley Area Lights
Boarding Lights Beacon Lights
Navigation Lights Water System
Toilet Lights

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2
Q

Electrical- Battery Master Switch

A

Used to connect the APU and main battery direct busses to the battery bus.

APU Battery 43 AMP
MAIN Battery 17 AMP
22 Volts Minimum
5 minute max without AC power for display cooling

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3
Q

Electrical- AC External Power

A

Used to select external AC power.

AVAIL light indicates external power is connected, is usable, and is ready to use.

IN USE light indicates that the
external AC power unit is supplying the electrical
system.

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4
Q

Electrical- IDG 1& IDG 2 Fault/ DISC

A

DISC-Used to DISCONNECT IDG
from Engine

FAULT- Indicates a fault
within the IDG
(HOT LOP) or Failure of the IDG to disconnect from the accessory gear box

DISC – Pressing DISC
Electrical solenoid is
energized that causes the
drive gear to retract from
the engine accessory gear
box. White DISC indicates Successful DISC

  • IDG will automatically
    disconnect when an
    Overtemperature or
    Overtorque Condition
    occurs.

Cannot reconnect IDG to Accessory gearbox in flight

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5
Q

Electric- AC ESS XFER

A

Used to switch essential bus feed from
AC bus 1 to AC bus 2.

ALTN light on indicates essential bus is fed
from AC bus 2.

Transfer is automatic during an AC bus 1
failure.

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6
Q

Electric- Gen 1/2 APU Gen Switches

A

OFF/ RESET - Disconnects generator
from associated bus and / or resets the
generator control circuit.

AUTO - Connects generator to associated
bus. (normal position)

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7
Q

Electrical- IDG AUTO XFER Fail/OFF

A

Used to Disable auto xfer of IDGs

Fail- light indicates a fault preventing auto
transfer. Reason could be GCU found in the IDG:
Over/ Under Voltage
Over/Under Frequency
Gen/BUS over-current
Generator out of phase

Off- Auto XFER is off

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8
Q

Fire Detection Firex Monitor Test button

A

The FIDEEX control unit monitors the fire
protection systems by automatically
performing periodic checks.

Before Start dont see APU FIRE FAIL MSG

TEST
x FIRE SYS OK

x MASTER WARNING

x LH / RH ENG FIRE PUSH

x BOTTLE 1 / 2 ARMED PUSH TO
DISCH

x APU FIRE PUSH

x BOTTLE ARMED PUSH TO DISCH

x FWD & AFT CARGO SMOKE PUSH

x BOTTLE ARMED PUSH TO DISCH

BATTERY MASTER switch needs to be
ON for a minimum of 30 sec to test.

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9
Q

What is FIDEX

A
  • Used to monitor electrical
    resistance of the loops.
  • When both loops experience
    same decrease in resistance
    “FIRE/OVHT’ msg. sent to EICAS.
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10
Q

Engine fire detection and extinguish

A

DUAL-LOOP DETECTION
* 2 Bottles AFT Equipment Bay
* Each bottle has 2 firing squibs
to extinguish engines.
* Both Bottles can be discharged
into one engine (buttons located on each side of glareshield

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11
Q

WHat happens: ENGINE FIRE PUSH button

A
  • Fuel SOV closes
  • Bleed air SOV closes
  • Hydraulic SOV closes
  • Engine driven generator
    is tripped off

Squibs on both FIREX bottles are armed

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12
Q

APU FIRE PUSH SELECTED

A
  • APU shuts down
  • APU Fuel Pump shuts
    off
  • APU LCV closes
  • Squib Armed
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13
Q

APU fire detection and extinguish

A

DUAL-LOOP DETECTION
* ON GROUND – APU Shuts
down automatically & 5secs
later bottle automatically
discharges.
* IN-FLIGHT – APU Shuts down
automatically BUT Crew must
discharge bottle.Bottle discharge located underneath apu fire push button

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14
Q

Cargo Firex

A
  • 3 Smoke Detectors FWD
    Compartment.
  • 2 Smoke Detectors Aft.
  • 2 FIREX bottles in the Right wing
    fairing “each bottle has 2
    squibs”
    One bottle is discharged
    immediately & 2nd Bottle
    discharges over time

We can only fight fire in one cargo compartment

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15
Q

MLG Fire detection

A

SINGLE LOOP DETECTION
* Continuously monitored
* Monitors Temperature in wheel
bins

NO Extinguishing, must put gear down.

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16
Q

L/R Hydrualic SOV button

A

Electrically-operated hydraulic
SOV.
* PURPOSE – interrupts the flow of
fluid from the reservoir to the
EDP.
* Used to close applicable HYD SOV
in event of a Hydraulic Leak or
overtemperature.
* Alternate method of closing the
Valves without having to shut
down engines to control fluid
overtemperature.

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17
Q

Fuel PUMPS are

A

DC ELECTRIC PUMPS that move fuel
from collector tanks to engines.
Used to back up the Main Ejectors
during engine start & when Ejectors
Fail.

IF one comes On they both come on

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18
Q

L/R Fuel Boost pumps ON/INOP

A

ON- Boost pump operating. When pressed you are only arming it So it will not initially turn white. automatically turns on when low fuel pressure is detected, like on an engine start(10 PSI or less)

INOP-
* Low Pump Pressure
* Pump Failure
* Pump not Armed (selected push out)

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19
Q

FFOD Fuel Check valve

A
  • One engine running, have
    to turn off boost pumps to
    prove fuel will not flow
    from left ejector to right
    engine or vice versa.
  • Should get
    “PUMP/PUMP/PRESS”

In normal ops if 1 boost fails, the other can get fuel to the failed pump side. Pumps have access to either side ejectors don’t that’s why when we turn both pumps off we want the pump pump press.

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20
Q

XFLOW AUTO OVERIDE MAN

A

Cancels auto xflow
(
White) Manual XFLOW is selected

FUEL imbalance caution msg. appears
if imbalance between wing tanks
exceeds 800lbs.
Used to override automatic powered

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21
Q

Gravity XFLOW FAIL/OPEN

When would we use this

and how

A

Disagreement light, if you have commanded a particular position and it is not in that position FAIL will come on

When pressed in GRAVITY cross feed line SOV opens and OPEN lights up. Pressed again VICE VERSA

When power XFLOW is not working. Slect MAN and Gravity XFLOW

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22
Q

When does powered xflow come on

A

imbalance of more than 200 pounds(No message appears) , will auto come on, valves open pumps turn on and fill low side from high side until excedance of 50lbs on the low side.

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23
Q

MAN XFLOW L/R ON/FAIL

A

L/R XFLOW ON- OPEN
and is operating
in the indicated
direction.

FAIL – powered
XFLOW has failed

These buttons will illuminate in manual and automatic if the xfer is happening

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24
Q

WING A/I CROSS BLEED

A

Controls the wing cross bleed valve

FROM LEFT - Wing cross bleed valve
open and right wing anti-ice valve closed.

NORMAL -Wing cross bleed valve closed.

FROM RIGHT - Wing cross bleed valve
open and left wing anti-ice valve closed.

USE when engine bleed valve fails, Wing A/I valve fails, Engine fails.

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25
Bleed Valves
Used to select bleed air mode. CLSD - Closes all bleed sources. ACSC is overridden. All valves are closed except external valve source. Must be selected when using external ground source to prevent damage to engines or APU. AUTO - Controller manages system requirements. MANUAL - Allows pilot to manually configure the system.
26
Bleed Valves in manual Mode
MANUAL - Allows pilot to manually configure the system. Used to isolate or interconnect the left and right pneumatic systems. Only operative in manual mode. Bleed Source- Used to select bleed source. L ENG - Left engine only BOTH ENG - both left and right engines R ENG - Right engine only APU - APU only ISOL ANF BLEED AOURCE only work in manual mode regardless of switch position
27
Bleed Valves in Auto
Bleeds on ground APU has priority for bleed source After thrust lever is out of TOGA, Gear up, and flaps less than 20, engines will have priority for bleed source
28
APU PWR FUEL
When pressed, APU fuel pump is energized and APU fuel shut--off valve opens, APU EICAS gauges and APU IN BITE message are displayed. On the ground, air inlet door is scheduled to open. PUMP FAIL light comes on to indicate that APU fuel pump has failed. SOV FAIL light comes on to indicate that the APU fuel shut--off valve has failed. When pressed again, APU fuel pump is de--energized.
29
APU START/AVAIL
SOV opens Open door BITE TEST MAIN BATT energizes ECU RPM and EGT gauges appear When pressed in: Start motor on START light comes on At 60% rpm, START light goes out AVAIL light comes on 2 seconds after APU reaches 99% rpm. When pressed out: Fuel shut--off valve closes APU shuts down AVAIL light goes out Air inlet door closes
30
Reason APU auto shut down
ON GROUND OR IN FLIGHT Fire Overspeed; RPM 107+ ECU Failure DC Power Loss Loss of RPM Signal Slow start ON GROUND / 60 SECONDS POST LANDING High oil temp low oil press intake door signal loss electrical short ON GROUND/APU BLEED UNAVAILABLE & 60 SECONDS POST LANDING Loss of EGT Signal
31
When does Green AVAIL come on APU start
99% PLUS 2 seconds
32
What are both Ignitions
IGNITION A powered by AC Essential bus IGNITION B powered by the Battery Bus through a static inverter
33
Engine L/R Start button when pressed
controls start sequence controlled by FADEC WHen pressed start vavle opens Both packs are turned off ISO valve opens ATS engages we get white status message
34
ENGINE L/R stop
Disengages respective engine starter
35
Engine start sequence N2 reaching 50%
ATS disengages Start valve closes AUTO ignition and On messages leave Packs are turned back on.
36
Continuous Ignition button
When pressed, activates A & B ignition systems on both engines.
37
Does Continuous Ignition button ever come on automatically
YES to prevent flameout near a stall, both ignitions come on since you are in flight
38
Engine Stop push button
Used to stop engine start sequence. STOP light indicates stop is selected. disengages the start on the engine
39
Hydraulic Pumps on panel what powers them
1B/3A – AC BUS 2 3B/2B – AC BUS 1
40
B pumps in auto mode
For (B) Pumps to come on * Associated BUS must be powered * FLAPS not at 0 * Generator Operating When main pump fails they do not automatically turn on, depends on configuration
41
B pumps in On
42
ACMP 3A
Used to control the operation of AC motor pump 3A. 2 position switch off on . ON - Pump will operate at 3000 psi output. with breaks included OFF - Pump inoperative.
43
ACMP 3B
Used to control the operation of AC motor pump 3B. Pump will operate irrespective of switch position when ADG is deployed. ON - Pump will operate at 3000 psi output. When main pump fails they do not automatically turn on, depends on configuration OFF - Pump inoperative. AUTO - Pump will operate in AUTO position, when flaps are greater than 0--degrees and either IDG 1 or IDG 2 is operating.
44
ACMP 1 and 2 B
Used to control the operation of AC motor pumps 1B and 2B ON - Pump will operate at 3000 psi output. OFF - Pump inoperative. AUTO - Pump will operate in AUTO position, when flaps are greater than 0--degrees. Avoid prolonged hydraulic system operations greater than 40° C.
45
Hydrualically, what happens when the ADG deploys
* ADG AUTOMATICALLY powers ACMP 3B to maintain hydraulic pressure to the primary flight controls. * PUMP 3B is automatically powered, during an AC power failure, by the ADG when it is deployed. * HYDRAULIC PUMP 3B will operate REGARDLESS of switch position
46
WHat does the ADG power
*ADG POWERS * * ADG BUS * AC ESS BUS * Hydraulic Pump 3B * Slats/Flaps half speed * Stab Trim
47
How is hydraulic systems cooled
System 1 & 2 cooled by a single oil heat exchanger. Cooling air from the ram air scoop is directed across the heat exchanger. Also cooling fan on ground
48
EMER DEPRESS button
Used to depressurize airplane during an emergency. ON light indicates emergency depressurization is selected. Outflow valve opens fully to dump cabin pressure. From the manual valve At cruise, valves dump to cabin pressure of 14500 ±500 feet. Restricts the cabin altitude to a max of 14,500 ± 500ft * ON – Airplane is depressurized * ON – Indicates outflow valve is commanded OPEN If aircraft is below 14,500ft the plane will depressurize CPCP(Cabin press control panel) controls Cabin Altitude to NOT EXCEED 15,000ft SMOKE in cabin or evacuation
49
PRESS CONT FAULT/MAN
Selects either manual or automatic control of pressurization system. FAULT light indicates failure of both cabin pressure controllers. Manual mode data is displayed on EICAS primary display. Automatic mode data is displayed on EICAS secondary display. When pressed twice, the redundant controller gains control. MAN - light indicates manual mode is selected.
50
LNDG Elevation
Used to set destination airport altitude. Setting indicated at LDG ELEV readout on Set highest altitude of either destination or departure.
51
MAN ALT
HOLD – Holds the set cabin alt. UP/DOWN – commands cabin alt to climb/descent. Controls pressurization in manual mode
52
MAN RATE
Controls the rate of change of the cabin altitude in manual mode Pneumatically adjusts outflow valve rate during manual mode. MAN ALT selected UP Range is 150 (±150) fpm to 4000 (±500) fpm. MAN ALT selected DN Range is -100 (±100) fpm to -2500 (±500) fpm.
53
Left (L) and Right (R) PACK Pneumatic air conditioning kit
Used to control the operation of air conditioning packs. UNLIT- it is on FAULT light indicates pack has failed in both automatic and manual modes. OFF light indicates pack is selected off. Single pack ceiling is 31,000
54
RAM air pushbutton
* Allows air from RAM air Scoop to enter the conditioned duct. * OPEN – RAIM AIR SOV open Used when both packs fail. Provides ambient air to LEFT conditioned air (cockpit) supply duct. OPEN light indicates ram air vent valve is selected open.
55
L/R MAN mode with the HOT COLD switch
manually control PACK temp. No overheat protection Used to operate air conditioning temperature control valves in manual mode. This way of controlling temp directly moves the Temperature control valve
56
RECIRC FAN
* Turns on both Recirc Fans & allows recirculated air to be mixed with conditioned air for Flight Deck & Cabin up to 34%
57
CKPT/CABIN Temp control knob
adjust temp in auto mode
58
AFT CARGO switch
* Controls air circulation in Cargo Bay * AIR – SOVs opened, Recirculated air ventilates aft cargo bay. * COND AIR - SOVs OPEN recirc air and conditioned air ventilate cargo bay (AFT) * ELECTRIC HEATER maintains bay temperature (60°F & 80°F) *PUPPY KILLER* OAT above 15° C, select AIR.
59
Wing Anti Ice
* ON - AILC operates modulating/shutoff valve to maintain leading edge within temperature range * Higher temp for Slats (piccolo Tube) FAILS CLOSED
60
COWL Anti Ice
* FAIL safe OPEN * Require air pressure from manifold & electrical power to close * T2 sensor probes in Engine Inlet
61
ICE TEST
DET / TEST Used to test the ice detection and air data sensor heating system. When pressed and held for 5 seconds; the master caution light flashes, the ICE caution message is displayed on EICAS primary page, the ADS HEAT TEST OK advisory message is displayed on EICAS status page, and the ICE light illuminates on the anti-ice panel. ICE light comes on to indicate that an icing condition has been detected and the wing and / or cowl anti-ice systems are not selected on.
62
Windshield heat
Used to control windshield and side window anti-ice systems. OFF/RESET - Removes power and resets the controllers. LOW - Used for de-misting and de- fogging of the windshield and side windows. HI - Used for de-icing of the windshield only. The side window remains at the low setting OAT above 30° C, select OFF on ground.
63
PROBES Inflight
* During Takeoff & WOW all Probes are energized regardless of probe switch position
64
Probes on ground
L/R pitot probe head - 1/2 power L/R pitot probe base- not heated Standby pitot probe- 1/2 power L/R AOA VAnes- OFF or full power L/R Static ports- OFF or full power TAT Probe - not heated
65
EMER LIGHTS
Used to control operation of emergency lighting system. ON - Turns on all emergency lights. OFF - Prevents actuation of emergency lights system. ARM - Emergency lights come on automatically if AC or DC essential power is lost.
66
67
What cools csd oil
N1 fan does most of the work. air oil heat exchange
68
Battery charger message on eicas
Bad, over temped or not working
69
When adv auto deploys do you have to pull the adg handle
Yes causes emergency contactors like the essential tie to open
70
Two times the essential tru 2 tie shows
Ac bus 2 lost and tru 1 fail contractor allows ac ess to power ess tru 2 Adg power ess tru 1 fails
71
Apu 2 minute cooling
To get fuel out and cool starter
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