Tests Flashcards
How are the fuel tanks normally vented?
The tanks are vented by vent lines in the collector tanks
Where is the aircraft fuel stored?
In the 2 main tanks and 1 center tank
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
Information:
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?
Scavenger ejectors
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?
FUEL IMBALANCE
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?
40 KVA
The main aircraft generators supply power to ______ AC buses?
4
Power for the 28 VDC is supplied by:
TRU’s
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:
4
Cranking power for starting the APU is provided by:
APU battery
The ADG supplies AC power to:
3B hydraulic pump
ESS AC bus
Slats/flaps and pitch trim
STAB CH2
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:
12,000 RPM
Fault protection for each engine is incorporated in each:
GCU
The priority for allowing power to AC Bus 1 would be:
IDG1
APU
IDG2
External AC
IDG2 normally powers:
AC Bus 2
Service Bus
The ADG can only supply power to:
3B hydraulic AC essential ADG Bus EICAS Slat, flaps, and pitch trim STAB CH 2
115 VAC is supplied to TRUs for DC static conversion, and each TRU is rated at:
120 amps
Which DC Bus tie(s) has(have) automatic operation?
MAIN TIE
CROSS TIE
ESS TIE
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:
Red
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?
Amber
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:
Green
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:
White
There are _______ types of aural warnings provided to alert the crew:
10
When the master warning lights are illuminated, pushing either switch will:
Cause both master warning lights to extinguish and reset for future
Warnings
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?
4
What components within EICAS collects and processes data from various aircraft systems?
DCU 1 and DCU 2
Where is the EICAS control panel located?
Center pedestal
Status and advisory messages displayed on the EICAS primary page?
False
Wingspan of the CRJ700?
76’ 3”
The exhaust danger area for the CRJ900 engines at idle thrust is?
100 feet
The overall length of the CRJ900 aircraft is?
118’11”
The CRJ900 maximum ramp weight is?
82,750 lbs
On the CRJ900, the distance from the top of the vertical stabilizer to the ground is approx?
24’ 1”
The danger area in front of both the CRJ700/900 with the radar operating is?
2 feet
The CRJ700 has a maximum steering angle of 80 degrees, the aircraft will require ________ feet to complete an 180 degree turn:
118’ 0”
The CRJ900 maximum takeoff weight?
82,500 lbs
The maximum load capacity of the passenger door is?
1000 lbs
The maximum number of people permitted on the stairway is?
4
Which of the following is NOT a “plug type” door?
Passenger 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:
6
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:
Electrical loads
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 LCV
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:
106%
Where is the APU located?
Tail cone
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:
14,750 lbs
What engine model is equipped on the CRJ900 series of aircraft?
CF34-8C5
Pneumatic bleed air is used for:
Air conditioning
The engines may be started using the APU, ground air source or engine cross bleed:
True
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:
50% N2
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?
Bypass air
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:
N1
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?
CLIMB
TOGA
MAX PWR
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
