Type Revision Flashcards
How can you check if the DV window is open
Check is the yellow pin is visible
Operation temperature limits
SAT -65 degrees, TAT -45 degrees
ELT – can be in auto or manual via panel in the cockpit
left side of the captain’s seat next to the DAP) or on / off switch on the transmitter itself
Speed trend vector is
10 seconds
Altitude trend vector is
6 seconds
ISIS time on battery
40 minutes
In a complete electrical failure standby instruments
9 minutes
Emergency lighting has (evacuation / crash situation)
15 minutes of power
CVR stops recording
When the parking brake is on
FDR starts recording
When the aircraft becomes airborne (WOW)
Cold dark cockpit (in flight)
all lights off and switches at twelve o’clock
DAU 1
FWD AIRPLANE SYSTEMS, FADEC 1A & 1B and LEFT ENGINE
DAU 2
AFT AIRPLANE SYSTEMS, FADEC 2A & 2B and RIGHT ENGINE
Take off phase inhibition
Valid from V1-15kts
Deactivated = radio altitude >400ft
Airspeed <60kts
Or 1 minute has elapsed
Aural warning unit levels (four)
o Emergency = triple chime every second o Abnormal = single chime every 5 seconds (e.g. traffic traffic) o Advisory = a single chime (one to go chime) o Information “aural unit ok” “aural unit one channel” “Aural unit one power” “trim” “Take off ok”
What are the basic modes of an airplane?
Roll & Pitch
Pink (magenta) =
White =
active mode
armed mode
Database is updated
Every 28 days by maintenance engineer
Flight plan is considered closed when
destination is the last / final waypoint
Pilot entered waypoint goes into the?
custom database (custom data maybe in the exam)
FMS button is pressed in order to?
drive lateral navigation (what button do we press on the mode control panel)
The CDU is the interface between?
The Pilot and FMS
If position is lost from all sensors or is inhibited, FMS goes into?
DR mode using AHRS / IRS, heading, airspeed and wind data. (AHRS is not on the circuit breakers it’s the IRS on there)
The AHRS / IRS get their power from?
DC Bus 2
The APU is available to provide power to the system after?
7 seconds after the APU accelerates through 95% RPM
Bus Tie Contactors (BTC) connect the APU and or GPU to the
Central DC Bus
Generators 1 and 3 provide power to the
left network driven by engine 1
Generators 2 and 4 provide power to the
right network driven by engine 2
Oder of priorities for the FMS
- GPS
- DME/DME
- VOR/DME
- IRS
During take-off and go-around one electric pump is required for each engine and the APU
Cross feed selector knob must be off for take-off
All the pumps are submerged via the
collector box being submerged
Purpose of the collector box is to?
prevent cavitation and it keeps the pumps submerged
Fuel system low level warning
210-265kg per tank
Fuel imbalance on each tank
363kg
EICAS caution is removed when the difference is less then?
45kg
Bleed air used for various aircraft systems
9th stage – always open
14th stage – commanded open
Fuel cooled oil cooler (FCOC)
Fuel is warmed, oil is cooled
The Lubrication system holds
12 quarts of oil (quantity checked on engine t/o data page on the MFD)
Always check this along
The Store button is pressed
4 times (alt t/o, temp, anti-ice on or off, stores data)
Air turbine starter commanded by the FADEC which?
controls the SCV which controls the air turbine starter (ATS) and starts engine.
How many FADECs?
2 FADECS A&B (Edna and Gladys) A = 1&2, B=1&2
If flaps fail
we can check on the RMU back up page and check the flaps and it will tell us where it has failed.
EICAS has a dash when the flaps are?
in transit / moving
Air-conditioning
Cockpit = pack one = 60% cockpit 40% cabin
Passenger Cabin = pack two = 100% cabin
Cross bleed valve can automatically switch to open
- During APU start
- Engine cross bleed start
- During ICE encounter
During an ice encounter below 24,600ft
the number 1 (left) pack will shut off – it will use its capacity for anti-icing.
The Air conditioning system consists of?
Recirculation fans x2
Gasper fan x1
Digital (electric) controller controls the?
Electro pneumatic valve
But slaved to the Electro pneumatic outflow valve is the pneumatic outflow valve.
Hydraulic system pumps
2 on each engine (1 electric and 1 mechanical) = 4
Hydraulic Fluid amount?
6 litres of Skydrol fluid
Quantity and temperature of hydraulic fluid are sensed
at the reservoir
Hydraulic Pressure is sensed at?
the manifold
Number one hydraulic system has a priority valve to maintain pressure for
aileron and flight controls
If the engine driven pumps drop below 1600psi the
electric pump kicks in
Electric pump pressure
2900 psi
What will the MFD system page show quantity (in a graph), pressure
(3000psi or 2900psi) and electric pump status
MFD system page doesn’t show
Temperature
Quantity of hydraulic fluid
green above 1 litre and amber below 1 litre
Hydraulic pressure range colours
Pressure green is in range, Amber and boxed below 1300psi or above 3300psi
if we have Total system failure
nose landing gear doors will open (because they are hydraulically locked up), Emergency brake only, no spoilers (don’t use speed brake)
The APU can provide
electrical (electricity) and Pneumatic and it can do it at the same time
Normal indications on the EICAS are
Green
The APU is controlled by
Electronic sequence unit (ESU) / FADEC
Switched on orange box comes on (3 seconds self-test)
Normal APU working load
400amps
The APU can provide power when over
95% (wait +7seconds in order to provide power to the buses)
The APU can withstand
600amps for 2 minutes
800amps for 5 seconds
Max APU start temp
884 degrees
Maximum APU starting limit altitude is
30,000ft
Maximum APU operation is
37,000ft
APU fire extinguisher
On the ground it automatically detects a fire it shuts down after 10 seconds
APU fire switch
- Signals ESU to stop (normal shutdown)
- Closes APU fuel shutoff valve
- Discharges the APU fire extinguisher bottle
