E170 System CBT questions Flashcards
What is the certified ceiling of the ERJ 170
41000 feet
In a turn, what requires the largest clearance
Tail
In case of total power loss,
DC power provide Emergency lighting
Above what cabin altitude will the NO SMOKING and FASTEN SEAT BELT signs automatically illuminate
14,000 feet
How many service doors provide access for service access
2
What is the max thrust of one engine
14,200 lbs
where is the EICAS display brightness control knob located
On the left hand glare shield light control panel
The warning message CABIN ALT HI together with a red cabin altitude indication will be displayed whenever the cabin altitude exceeds
9700 ft.
Cabin zone temperature control
can be transferred from the cockpit control panel to the flight attendant control panel
Pushing the dump switch on the pressurization panel in the cockpit
will depressurize the cabin to a maximum of 12,400 ft. cabin altitude, and deactivates the recirculation fans and the ECS packs
During normal operation, the conditioned air consists of
52 percent fresh air and 48 percent recirculation air
Which of the following components regulate the air flow to the ECS packs
the Flow Control Valve
During cruise below 37,000 ft. the normal differential pressure is limited to
7.8 PSID
The CPCS calculates a target cabin altitude for each of the following CPCS flight modes
ground, taxi, takeoff, climb, cruise, descent, and abort
The positive pressure relief valve (safety valve) opens independently whenever the differential pressure exceeds
8.6 PSID
The cabin pressure control system consists of the following main components
one cabin pressure controller, one cabin outflow valve, one negative relief valve, one positive pressure relief valve, and one static port
The emergency ram air valve is commanded open
I Pack1 and Pack2 are commanded/failed OFF, and the altitude is less than 25,000 ft.
During a normal APU shutdown what services are available
no services are available
Pushing the emergency stop button on the APU panel causes what
APU to stop immediately
What causes the APU to automatically shut down on the ground
All of the above
- Overspeed, FADEC critical fault
- APU fire, EGT over temp, sensor failure
- APU high oil temp, APU low oil pressure
What is the maximum altitude for starting the APU
30,000 ft.
What is the max altitude for conditioning air operation from the APU
15,000 ft.
What actions trip the autopilot
All of the above
- manual trim or quick disc switches activated, column shakers are activated
- the fly by wire system in direct mode, aileron and elevator system disconnects
- a column and control wheel force monitor sensor trips
Pressing the NAV button the FMA annunciator displays
LNAV, LOC
The guidance panel provides what functions
All of the above
- lateral and vertical guidance control
- AFCS management control
- two independent A and B channels
Pressing the centre of the ALT selector knob does what
Provides the selected ALT in METERS to be displayed on the PFD
Pressing the back up trim switch with the autopilot engaged
the autopilot disconnects
Can you reconnect the IDG in flight
no
When IDG1 and IDG2 are selected off
the generator is de-energized and the line contactor is open
What does the AVAIL lamp on the overhead electrical panel mean
the external power is connected and all quality requirements are satisfied
If the APU is available and one engine generator fails, the failed generator is replaced by
the APU generator
The STBY AC BUS is normally powered by the ESS AC BUS. It will be powered by the inverter,
when the aircraft is powered by batteries only
Each thrust reverser half has
2 hydraulic actuators
How many ignitors are energized for each engine start
one on ground and two in flight
What controls the Fuel Metering Unit
the FADEC
What type of engine is the General Electric CF34-8E
High-Bypass two spool turbofan
During normal engine start
the FADEC opens and closes the starter control valve automatically
Pushing the test button on the fire extinguisher panel in the cockpit will
test the engine and APU fire detection as well as the cargo smoke detection system
When smoke is detected in the forward lavatory
all statements are correct
- an alarm will sound and the red alarm indicator will illuminate
- an EICAS warning LAV SMOKE will be displayed in the cockpit
- the flashing amber lights on both the attendant light indicator panels will be activated
Pulling down an Engine fire handle in the cockpit will
shutoff the fuel system, hydraulic fluids, and the bleed air system of the respective engine
In the event of an APU fire on ground
the APU will shut down after 10 seconds, if there is no commanded shut down through the APU emergency stop switch
The lavatory fire extinguisher is
activated automatically when a certain temp has been reached
The HS-ACE responds to
trim commands from the backup trim, pilot trim, Co-pilot trim, and FCM trim inputs
What is the correct sequence of slats/flaps extension and retraction
slats extend first, while flaps retract first
The elevator thrust compensation (ETC) function, stabilizing the aircraft around the pitch axis, will be available
in normal mode only, as it is computed in the FCM unit
The two aileron PCUs per side operate the aileron surface,
in an active/active configuration
Hydraulic system 3 powers which elevator PCU
Right outboard
A single trim command fro yaw and pitch is limited to
3 seconds
Following a jammed control column (pitch), when the elev disc handle is pulled,
the unrestricted control column controls its own side elevator
The flight control system can operate in normal or direct mode. Which of the following statements concerning the two different modes is true
in direct mode, FCM commands are removed from the control loop
Which of the following systems are NOT driven by fly-by-wire technology
the ailerons only; all other systems are driven by fly by wire technology
In case of a single electric motor failure within the flap PDU how will the system operate
the flap/slat system will operate at low rate speed
How many minutes of cockpit audio can the DVDR record
120 minutes
what is the primary means of radio tuning
MCDU
What powers the IESS in case of electrical emergency
RAT or Batteries
During normal operation, air data readouts on the captains PDF are from which ADS
ADS 1
the IESS can display which of the following
all of the above
- Attitude, Altitude, and IAS
- Mach, VMO/MMO, slip indication, VS
- ILS, barometric pressure, Altitude in meters
The PTU transfers hydraulic power from system 1 to system 2 to guarantee normal operation of which system
landing gear
how many electric hydraulic pumps are used for each system
system 1 and 2 have one electric hydraulic pump each, system 3 has two electric hydraulic pumps
the EMBRAER 170 hydraulic system operates at what nominal pressure
3000 psi
What does SECTOR SCAN on the weather radar do
reduces the sweep angle to -30 degrees and increases the sweep rate to 24spm
the Air data system comprises of what components
4 ADSP’s, 2 TAT probes, 3 ADA’s, and the Baro set on the GP
Which IRS is the primary source for the captain PFD
IRS 1
When will a Fuel imbalance caution message be displayed on the EICAS
whenever a lateral fuel imbalance exceeding 360 kg (800 lbs) exists.
What is the purpose of the wing surge tanks
The surge tanks collect the fuel during wing-down or uncoordinated flight maneuvers
With the engines running, through which pumps are the engines and the APU fed
the primary ejector pumps
the DC fuel pump,
is located in the right wing tank and can be used in fight and on the ground
to correct lateral imbalances using the crossfeed function, the pilot must
select the XFEED switch to the LOW1 or LOW2 position, while the two AC Aux pump switches must remain in AUTO
Which electric hydraulic pumps are automatically switched on for take-off or landing
system 1 and 2
Hydraulic system 3 powers which flight controls
Rudder, right elevator and both ailerons
If only a single power source is available and both windshields are operative, which windshield system is powered
Left
With the Ice detection mode selector knob set to AUTO and the T/O DATASET “REF A/I” set to OFF,
the wing A/I system is inhibited until 1700’ ALG or 2 min after liftoff
Following automatic activation and when icing conditions are no longer sensed, how long will the wing and engine anti-ice systems remain active
5 minutes
When the ADSP and TAT probe heaters powered
Whenever the engines are running
With the ice detection mode selector knob to ON, when will the engine A/I systems operate
whenever the engines are running
During normal operation, the landing gear system is
electronically controlled and hydraulically operated
Towing is NOT allowed when
all of the above
- the steering motor is pressurized
- when operation is in active mode
- if any of the brakes are pressurized
In the event of a failure in the PSEM electronics, the landing gear should be extended by means of
the electrical override switch
Which BCM protections are still available during auto-brake control
Anti-skid control, touchdown protection, locked wheel protection
In the event of a failure of both electronic and the electrical override system, the landing gear should be extended by means of
the alternate gear extension lever
Where is the crew oxygen pressure indication
on the status synoptic page on MFD
Above what cabin altitude will the passenger oxygen system deploy automatically
14,000 ft.
How can you activate the microphone in one of the pilots oxygen masks
open the door of the stowage box or press the Test/Reset button
Where is the flight crew oxygen cylinder stored
in the forward cargo compartment
If activated the chemical oxygen dispensing units supply oxygen for a passenger for a period of approx.
12 minutes
TCF (terrain clearance floor) function is based on airplane present position, radio altitude, and
distance to the nearest runway on database
The system which provides information and alerting to detect a potentially hazardous terrain situation in order to prevent CFIT is
EGPWS
EICAS message that requires immediate crew awareness and a subsequent corrective action is
CAUTION
EICAS messages are sometimes inhibited to prevent it from being a nuisance. K2b coded messages are inhibited
on takeoff roll
EICAS STATUS messages are displayed in
white
