Flashcards in Tests Deck (280):
Where is the aircraft fuel stored?
In the 2 main tanks and 1 center tank
How are the fuel tanks normally vented?
The tanks are vented by vent lines in the collector tanks
How are the fuel system faults annunciated?
Switch lights on the overhead fuel panel
On EICAS in the form of messages
What is used to provide the fuel system computer with fuel quantity
6 fuel quantity probes with compensator units in each main tanks
3 probes in the center tank
What type of ejector pumps are used to move fuel from the main tanks to the collector tanks?
What maintains fuel symmetry between the main tanks?
Automatically controlled by the Bi-Directional X flow pump
How are the collector tanks kept full?
Gravity feed lines and scavenge ejectors
What is used to back up the main ejectors?
2 electric boost pumps
The electric fuel boost pumps....
Are energized during engine start
Can feed fuel to either engine from one collector tank
Back to the main ejector pumps
From what source is APU fuel feed supplied?
From the left collector tank via APU fuel pump
Where is the bulk temperature taken?
Right main tank
How is pressure refueling and suction defueling accomplished and how is it controlled?
Accomplished through the single point refuel/defuel adapter. Controlled from the refuel/defuel control panel
If a fuel asymmetry condition exists between the two tanks, what visual caution message is presented in EICAS?
What fuel system information is displayed on the EICAS Primary page?
Individual tank quantities, total fuel quantity, fuel used quantity
For automatic pressure refueling, what does the refuel/defuel control panel permit?
Preselection of fuel quantity desired
Built in test (BITE) feature
Refuel/defuel shut-off valves to close automatically if the maximum fuel level is reached
The engine driven and APU generators are rated at?
The main aircraft generators supply power to ______ AC buses?
Power for the 28 VDC is supplied by:
The APU battery is:
24 volts rated at 43 amp/hours
The main battery is:
24 volts 17 amp/hrs
TRU's supply power to ______ DC buses:
Cranking power for starting the APU is provided by:
The ADG supplies AC power to:
3B hydraulic pump
ESS AC bus
Slats/flaps and pitch trim
The main and APU batteries are kept in charged condition by battery chargers powered by:
AC BUS No. 1
AC Service Bus
The external AC power receptacle is located:
Forward right side of the aircraft
Electrical systems warning and caution messages are normally displayed on:
EICAS primary page
Electrical system status and advisory messages are normally displayed on:
EICAS status page
The IDG provides a means of converting:
Variable engine speed to constant generator speed
The IDGs may be disconnected from the gearbox by:
Disconnect switches located in the cockpit
Once disconnected, the IDG:
Can only be manually re-connected on the ground with engine shutdown by MTX
The IDGs convert variable engine speed to:
Fault protection for each engine is incorporated in each:
The priority for allowing power to AC Bus 1 would be:
IDG2 normally powers:
AC Bus 2
The ADG can only supply power to:
Slat, flaps, and pitch trim
STAB CH 2
115 VAC is supplied to TRUs for DC static conversion, and each TRU is rated at:
Which DC Bus tie(s) has(have) automatic operation?
In flight, the ADG Auto deploy monitors the three main AC generators and the main AC Buses for:
Complete AC power failure
An amber IDG fault light/caution light indicates:
Low IDG oil pressure and/or high IDG oil temperature
An AUTO XFER fail light ( amber) on the Electrical panel indicates:
Generator over current or a bus fault
An AC ESS XFER light (white) on the Electrical panel indicates?
AC ESS Bus is not being powered by AC Bus 1
What are the generators rated at?
40 KVA up to FL410
Warning messages will always appear as a _______ message on the CAS:
When warning messages are displayed, they will be accomplished by:
Flashing master warning, aural alert, and voice advisory if applicable
Caution messages will always appear as a _________ message on the CAS?
Caution messages will appear immediately:
Below warning messages
When caution messages are displayed, they will be accomplished by:
A flashing master caution light
Warning and caution messages will normally appear on the:
EICAS primary page
Advisory messages will always appear as a _________ message on the CAS:
Advisory messages are always displayed:
At the top of the stack on the status page
Status messages will always appear as a ________ message on the CAS:
There are _______ types of aural warnings provided to alert the crew:
When the master warning lights are illuminated, pushing either switch will:
Cause both master warning lights to extinguish and reset for future
Data Concentrator Units (DCU) are located in the Avionics bay and are used to:
Process and transmit aircraft sensor data to the FDR And EICAS lamp driver unit
What is the function of the EICAS?
Provide crew with visual and aural crew alert messages and real time interpretation of aircraft system
How many levels of CAS importance are there?
What components within EICAS collects and processes data from various aircraft systems?
DCU 1 and DCU 2
Where is the EICAS control panel located?
Status and advisory messages displayed on the EICAS primary page?
Wingspan of the CRJ700?
The exhaust danger area for the CRJ900 engines at idle thrust is?
The overall length of the CRJ900 aircraft is?
The CRJ900 maximum ramp weight is?
On the CRJ900, the distance from the top of the vertical stabilizer to the ground is approx?
The danger area in front of both the CRJ700/900 with the radar operating is?
The CRJ700 has a maximum steering angle of 80 degrees, the aircraft will require ________ feet to complete an 180 degree turn:
The CRJ900 maximum takeoff weight?
The maximum load capacity of the passenger door is?
The maximum number of people permitted on the stairway is?
Which of the following is NOT a "plug type" door?
A red warning message on EICAS would indicate that:
The passenger door is not locked properly
In the event of passenger evacuation on the CRJ900, there are ______ emergency exits available:
The correct eye reference position for pilot or copilot seat adjustment is indicated when:
The white ball appears in center of orange ball
The APU is equipped with a:
40 kVA generator
The APU supplies pneumatic power for:
Main engine starts and air conditioning
The APU ECU controls the APU during:
All phases of operation
The APU control system ensures priority is given to:
Pressurized fuel is supplied to the APU by the:
APU fuel pump
What is the purpose of the internal bypass valve?
Allows the APU to continue to run if APU pump fails
APU RPM is displayed on the:
EICAS Status page
APU bleed air is controlled by modulating:
APU bleed pressure readout can be monitored on:
EICAS "ECS" synoptic page
APU "AVAIL" will illuminate at:
99% RPM and 2 seconds later
The APU gauges (RPM and EGT) appear on EICAS when:
APU POWER/FUEL switch/light is pressed in
"APU OVERSPEED" warning message is displayed when RPM exceeds:
Where is the APU located?
APU intake door is located:
Upper right hand side (aft) aircraft
APU secondary functions:
Supplies bleed air for air conditioning
Supplies air for main and engine starting
If APU door position is unknown, airspeed is restricted to:
220 KIAS and APU is not operating
The APU door position is displayed on the:
EICAS Status page
The CF34-8C5, with APR, has a thrust rating of:
What engine model is equipped on the CRJ900 series of aircraft?
Pneumatic bleed air is used for:
The engines may be started using the APU, ground air source or engine cross bleed:
When does the APR system arm?
When the engine speed is within 8% N1 scheduled takeoff power
During an engine start, the starters cuts out at:
Refilling of the oil system is provided by a replenishment tank:
Located in the aft equipment bay
Engine oil is cooled by:
Fuel/oil heat exchanger
80% of engine thrust is generated by?
When will OEO thrust be activated?
N1 mismatch 15% RPM
The left engine is the master engine for:
N1 and N2 Sync
The primary thrust setting reference is:
With Wing anti-ice on, the N2 RPM Indicators will:
Turn White from 0 to 77% RPM
The left engine START switch light, when pressed in:
Opens the left bleed air Start Valve and the isolation valve
Prior to takeoff, normal rated takeoff N1 thrust is displayed...
Automatically by FADEC
The thrust lever quadrant is equipped with detente located at what positions?
Which hydraulic system is used during normal landing gear extension and retraction?
#3 hydraulic system
With the aircraft on the ground, what is incorporated within the landing gear control lever to prevent an up selection?
A solenoid lock
During the landing gear retraction sequence, why is hydraulic pressure from the nose landing gear up line routed to activate the brake control valves?
To stop main wheel rotation
What means is provided to mute the landing gear horn?
Horn mute switch/light on the landing gear control panel
Where are the landing gear position and status displayed?
EICAS Primary page (ED1)
The alternate landing gear extension method should be used in case of a failure in the landing gears control system or:
#3 hydraulic system
Pulling the landing gear manual release handle will permit the MLG to extend and lock into position:
Using gravity and down lock assist actuator force from the no. 2 HYD system
What powers the wheel brakes?
No. 2 HYD system powers the O/B brakes and the No. 3 HYD system powers the O/B brakes
In the event of a failure of No. 2 and No. 3 hydraulic power, what emergency braking is available?
Brake accumulators in both hydraulic systems provide reserve pressure for 6 brake applications with anti-skid selected OFF
Where is brake pressure displayed?
On EICAS Hydraulic synoptic page
When the parking brake is applied hydraulic pressure is trapped within which brake system?
Only the I/B brakes
Monitors the temperature of each brake and the information is displayed on EICAS
Provided the anti-skid is armed, when does it become operational?
Once a 35 knot wheel spin-up signal is present or a WOW signal after a 5 second delay
When using the steering tiller, nose wheel steering is available through how many degrees?
The strike indicator located in the FWD end of the tail bumper assembly is there for.....
Visual indication of a tail strike
Landing Gear position indicators are located on the.....
MLG doors are.....
Pump 3B is automatically running when the ADG is deployed (T/F)
With the switch in the AUTO position, Pump 3B will be operating during normal take offs and landings (T/F)
What is normal hydraulic system pressure?
What ACMP is directly powered by the ADG?
What is the normal percentage of hydraulic fluid in the system?
AC-motor pumps 1B and 2B will automatically turn on during an engine failure (T/F)...
Where would you normally be able to read hydraulic brake pressure?
On the hydraulic synoptic page
Where can the hydraulic systems be viewed on EICAS under normal operating conditions?
The EICAS hydraulic synoptic page
What activates the hydraulic shut off valve at the engine firewall?
ENGINE FIRE PUSH switch light
HYD SOV switch lights on overhead pane
When the hydraulic pump switch 1 and 2 are set to AUTO, when will the pumps automatically start?
Flaps are in the 0 degree position
Any generator on line
Which hydraulic pumps are engine driven?
1A and 2A
How are hydraulic systems #1 and #2 cooled?
Ram air/oil heat exchanger
Systems 1 and 2 are each powered by and EDP and an AC PUMP (T/F).....
System #3 is powered by ________ AC -motor pumps:
With normal switch positions, which electric hydraulic pump normally operates continuously?
How many hydraulic systems are normally used to power the rudder?
The CRJ has __________ hydraulic pumps?
6 - 2 engine-driven and 4 electric
At cruise, normally which hydraulic pumps are operating?
1A, 2A, and 3A
You are taxiing out single engine (right engine running), which hydraulic
Pumps are running in normal operations (flaps up)?
2A and 3A
With the No. 1 engine shutdown in flight, which hydraulic pumps are not available?
The A pumps are engine-driven, and the "B" pumps are electric AC motor-driven (T/F)?
What is considered low hydraulic pressure?
< 1800 PSI
What is considered high hydraulic pressure?
> 3200 PSI
When does hydraulic pressure relief occur?
> 3750 PSI and excessive fluid is vented to an overflow bottle
What aides the crew in directional control during a jammed rudder conditions?
Rudder system anti-jam/breakout mechanisms
The purpose of aileron flutter dampers is:
Prevent control surface flutter when hydraulic power is lost to the PCUs
What are the takeoff flap settings?
8 and 20 degrees
The elevators, rudder and ailerons are:
Manually controlled and hydraulically actuated
What is the purpose of the aileron bungee breakout switch?
Provides automatic on-side MFS control to operable circuit during aileron PCU runaway
What/Who has the highest priority when trimming the horizontal stabilizer trim?
HORT STAB trim limits?
+2 degrees to -13 degrees
A SPOILERONS ROLL caution message, accomplished by amber ROLL SEL lights on the glare shield indicates?
Roll disconnect handle has been pulled, but spoileron priority has not been established
What are the selectable flap positions?
What message appears on EICAS if one flap motor fails?
Flaps half speed
During landing or rejected takeoff, how does multifunction spoilers deploy logic differ from ground spoilers deploy logistic?
Multifunction spoilers deployment requires R and L MLG WOW
In the event of total AC electrical power failure, the flight controls will remain operational because ACMP 3B is powered by the ADG bus (T/F)?
Each elevator is hydraulically powered by ___________ PCUs
Bleed air is used for?
Engine cowl anti-icing and wing anti-icing
The left and right Pitot/Static probes are?
When the WSHLD switch is set to LOW:
The side windows are in low
Ice detection probes are:
Ice detector switch/light illuminates amber it indicate aircraft entry into icing with:
Wing and cowl anti-ice off
The windshield wipers operate:
Together, at the last speed selected by either pilot
At what point does the Air Data Sensor Heater Control energize all probes and sensor heater regardless of probe or generator switch position?
The windshield wipers will operate at the most recently selected speed (T/F)?
Ice and Rain protection systems displayed Caution/Warning, Advisory/Status Messages on:
EICAS Primary and/or Status page
What does the DET TEST SWITCHLIGHT test when pressed?
Ice detectors and air data probes and sensor heaters
The right hand pack normally supplies the :
RAM AIR ventilation is used only when:
When the aircraft is unpressurized
Cabin air outflow is controlled automatic by:
The active CPC maintains aircraft pressurization
The pressurization system automatically pre-pressurizes the aircraft to:
- 150 feet
Maximum negative pressure differential pressure is:
- 0.5 PSI
If the cabin altitude reaches 14,000 feet the:
CPAM will trigger the oxygen system auto deploy to the passengers
On the ground, with Display Control Panel in Normal, what cools the cockpit displays?
When the PRESS CONT switch/light is pressed in:
It selects manual mode
The manual cabin altitude regulator, when selected UP:
Causes the outflow valve to open and increase cabin altitude
When in Manual (MAN) the pressurization read outs are displayed on:
EICAS Primary page
The two safety valves located on the aft pressure bulkhead:
Provide over/under pressure relief
During ground operations the ground valve:
Is controlled from the Avionics Fan Switch
What is the normal source for engine supply bleed air to the manifold?
6th or 10th stage
The aircraft has ______ independent built-in oxygen systems
The flight compartment oxygen bottle has a _______ capacity:
50 cu ft
The flight compartment oxygen bottle is normally charged to:
Over pressure relief for the flight compartment oxygen system will occur at:
The "OXY LO PRESS" caution will be displayed on EICAS when the pressure is below:
The Normal/100% Lever on the Pilots Mask Stowage Container should be set to:
The indications of oxygen flow from the flight compartment mask can be confirmed by:
Yellow cross appears on the blinker
The oxygen mask regulator will supply 100% continuous flow above a:
30,000 ft cabin altitude
The PBE hood provides oxygen for approximately:
Passenger oxygen masks will automatically deploy if the cabin altitude exceeds:
A crash axe is located:
Behind the co-pilots seat
On the CRJ900, the four emergency exit windows over the wing open:
Inward from the top with adjacent life lines
The CRJ900 emergency lighting system is provided by five rechargeable battery packs that will supply power for approximately:
The emergency lights can be:
Armed or turned on from the flight compartment
Turned on from the flight attendant panel
Flight crew members life vests are:
Stowed beneath each crew members seat
Fire detection and extinguishing is provided in the:
Left and right core sections and APU compartment
When the heat sensing elements are subjected to heat, the:
The fire detection system for the engines use:
A dual loop sensing element mounted in parallel
The cargo compartment has:
3 smoke detectors in FWD
2 smoke detectors in AFT
The engine firex bottles are located in the:
Aft equipment bay
An APU fire on the ground will cause:
Shutdown the APU, automatically discharge the firex bottle and display an EICAS message
The lavatory firex bottle is discharge by:
Heat sensitive capsule automatically
When a fire warning is detected, the MASTER WARNING light flashes, a fire bell sounds, an EICAS message appears, and the appropriate
Engine fire push light illuminates red. Pushing the ENG FIRE push light "IN" will:
Arm the dedicated squibs to the affected engine
Close the fuel, hydraulic and bleed air shut off valves
Shutdown engine driven generator
Engine fire messages are displayed:
EICAS primary page
The fire bell can be silenced by pushing "IN" on the:
Master warning switch light
ENG BOTTLE LO messages are displayed on:
EICAS status page
What two subsystems comprise the Fire and Overhead Protection System?
Fire Overheat Detection System and Fire Extinguisher System
What unit controls the Fire Protection, Smoke Detection, and Fire Extinguishing system?
The FWD/AFT Cargo Bays have both Smoke Detection and Fire Extin guishing equipment (T/F):
Engine and APU Fire/Overheat Detection is accomplished by _______
Loop(s) in the engine area and APU compartments:
A Fire Warning is generated when one or more fire loops sense an overheat condition (T/F):
A Squib fires to release Halon into the lavatory waste bin (T/F):
Fire Overheat/detection loops consist of two wires inside a metal sheath separated by _________:
An insulating material (thermistor)
The __________ can discriminate between a real and false fire indication:
FIDEEX Control Unit
What happens when the LH or RH ENG FIRE PUSH SWITCHLIGHT is pressed?
Bottle squibs are armed
Hydraulic SOV closes
The APU bottle will automatically discharge in flight if an APU fire is detected (T/F):
When the respective CARGO FIREX BOTTLE ARMED PUSH TO DISCHARGE switch is pressed:
One bottle will discharge completely, and the other discharges slowly over an extended period of time
The audio control panels are located on the center pedestal (T/F):
The MASK/BOOM switch is located on the audio control panel (T/F):
The ELT is located in the tail section of the aircraft (T/F):
How is tuning the ADF receivers achieved?
Through the RTUs
How many ADF receivers does the CRJ have?
The FMS Tune Inhibit switch:
Inhibits the FMS radio
Which radios can be tuned by the back-up tuning unit?
When does the high/low chime sound in the flight deck?
When a call is initiated to the flight deck from the FA station
During use of the PA system, who has the highest priority?
FA to flight deck calls are indicated by a steady CALL SWITCHLIGHT illuminated on the center pedestal (T/F):
Pressing the CALL SWITCHLIGHT in the flight deck will signal the FA with an illuminated SWITCHLIGHT on the handset and a:
High/low chime in cabin
Pressing the CHIME SWITCHLIGHT from the flight deck will:
Generate a high/low chime in the cabin
To squawk IDENT, push the IDENT button on either RTU (T/F):
COM2 can be tuned using:
FMS radio page
Selecting various flight director modes is accomplished through the:
Flight Control Panel
The primary purpose of the altitude preselect mode is to:
Generate commands to capture and track the preselected altitude
Lamp lights on each side of a mode push button indicates:
That FCC1 and FCC2 have acknowledge that mode input
If a new flight director mode became active, the annunciation in the FMA will:
Flash green for 5 seconds then steady
When the transfer (XFR) switch on the flight control panel is selected:
The co-pilots flight director provide guidance to the autopilot
Pressing either TOGA switch on a thrust lever will:
Disconnect the autopilot
When the turbulence push button is engaged, the autopilot will:
Reduces autopilot gain
The flight director sync switch (on the control wheel):
Synchronize flight director references to those currently flown
The flight director command bars can be flown:
By the autopilot
The color of an ARMED flight director mode in the flight mode annunciation is:
If you engage the ALT mode push button on the FCP, the FD will:
Generate commands to maintain pressure altitude existing at time of selection
To set the Heading Bug on the PFD and MFD, the Pilot must use the HDG Rotary Knob on the:
Flight Control Panel
At what pressure altitude will half bank be automatically activated?
Which is not a way to disconnect the autopilot?
Activating the aileron trim switches
In takeoff mode (TOGA) how much bank authority is given to the FD?
In the event that a PFD fails, PFD information can be displayed on the MFD by using the:
Reversionary Mode Switch
The TAT Probe supplies temperature information to the:
Air Data Computers
Pitot/Static inputs and TAT provide raw Air Data information which is converted to digital format through the:
Air Data Computers
What is the time required to align the AHRS in the MAG Mode?
What is the time required to align the AHRS in the DG Mode?
Radio altitude will be displayed on the PFD below:
2500 feet AGL
The Airspeed trend vector indicates the predicated airspeed in:
The MACH number will be displayed when the aircraft reaches:
The Green Line on the Airspeed Tape indicates?
The Slop and Skid indicator on the PFD is:
A rectangle under the Roll Pointer
When a common Attitude/Heading source is selected, an annunciation will appear on the:
PFD and MFD
The Integrated Standby Indicator can display Localizer and Glide Slope information (T/F):
The ISI is located:
In the Center Instrument Panel
The Co-pilots PFD and MFD normally receives Air Data, Attitude, and Heading information from the:
ADC2 and AHRS2
Where is the radar control panel mounted?
The EGDWS alerts and warns the flight crew when the airplane's flight path and positive relative to _______ requires immediate crew attention and action
How are being pointers displayed?
Selected through the Display Control Panel
Weather radar returns, when selected, are displayed on the MFD's (T/F):
The ________ is an airborne system that interrogates ATC transponders in nearby airplanes to identify and display potential and predicted collision threats.
TCAS monitors a radius of approximately ______ NM about the airplane:
Each of the MFDs has the primary function of showing:
Each PFD has the function of pictorially showing:
Flight control system mode annunciation a
When will the vertical deviation glide scale (Green Diamond) be displayed on the PFD and MFD?
When a valid ILS is tuned
With a (RED) Windshear warning you would expect:
Decrease in flight performance with escape guidance
If the TCAS system produces an Aural of "Traffic, Traffic"' what symbol would be associated with it?
An amber circle
Wind shear warning will stop when:
Wind shear conditions are no longer present
With an (Amber) Wind Shear Alert you would expect a(n):
Decrease in flight performance with escape guidance in GA mode
Which colors are used by the RADAR system, starting with the most precipitation levels to the least amount of precip
Magenta, Red, Yellow, Green, Black
Where are the RADAR returns displayed?
The pilot can cancel a "SINK RATE" advisory by:
Pressing the GPWS switch
Climbing the aircraft above the trip point