Exam Q's Flashcards
Where is the main access panel for the main electrical compartment?
Inside the nose landing gear compartment
The backup battery is powered by the :
Emergency DC bus 2
The main generators are connected to the electrical system by :
Main generator contactors
Is the APU available for use if the electrical system is in the emergency mode?
No. The system must be set to “Normal” to use the APU.
The “TEST” position on the backup battery switch simulates:
Emergency DC bus 1 failure.
Are the AUX generators identical to the MAIN generators?
Yes
A short circuit in the central DC bus results in loss of:
- Engine/APU Air start capability
- Battery charging
(Due Central bus disconnected)
When will the electrical system automatically switch from NORM to EMERG mode?
- At least one main generator switch on
- PWR SELECT switch in BATT
- Both main generators loss
(after a 2 second delay)
What are the two modes of operation for the aircraft electrical system?
Normal and Emergency
What could you assume if both the 26v “AC BUS OFF” lights are illuminated?
Only the 26v output of inverter #1 has failed, therefore to enable auto switching it must be turned off.
When will the FORWARD ACTUATOR light illuminate?
When the forward door is hydraulically blocked.
How many exits does the EMB120 have in the passenger cabin in case of emergency (including normal doors/exits)
4
Can the direct vision windows be removed by the crew?
Yes
How can you raise/lower the forward door?
Normally - Raised hydraulically, lowered manually
Can be raised and lowered manually also in case of hydraulic failure.
How many cycles can the forward door be operated without recharging its accumulator?
4
The transfer jet pumps are utilised to :
Keep the collector tank full.
A flashing fuel pump ON light indicates:
The pump is cycling (Automatically below 9PSI)
Firewall fuel shutoff valves are controlled by?
The Fire T Handles.
How is the collector tank kept at a constant level during normal flight?
- Two scavenger jet pumps
- Gravity feed
What will cause the emergency lights to illuminate?
- A failure of Emergency DC bus 1
- Placing Cockpit switch to ON
- Leaving Cockpit switch in ARM before turning PWR SELECT switch off
- CA Switch to on
- CA switch to test (Simulates emergency DC bus 1 failure)
What does a white light indicate when illuminated on the cabin attendants discrete call panel?
A call from the lavatory.
With the courtesy switch in the AUTO position what will happen?
The courtesy lights will illuminate when the main door is open regardless of the position of the PWR SELECT switch. (Hot battery bus)
Describe the power for the emergency lighting system?
Power is supplied from 3 rechargable battery packs,
Normally recharged from Emergency DC bus 1. They will illuminate with a failure of emergency DC bus 1 (Total electrical failure)
The batteries will last 17minutes and take approximately 22hrs to recharge.
When will the DOORS light illuminate on the MAP?
- Main cargo door open
- Forward entry door open
- Any service door open
When will the CABIN ALT light illuminate?
When the cabin altitude has exceeded 10000ft.
Can you cancel the aural warning for landing gear not down and licked with flaps extended past 17*?
No
What aural warnings can be heard for incorrect takeoff configuration?
- TAKEOFF BRAKES, TRIM, FLAPS, AUTOFEATHER
What does a aural “BATTERY” warning indicate?
Battery overheat condition >70*c
In most cases what happens when you press the Alarm cancel button?
Will cancel MASTER/CAUTION lights and the respective associated aural warning. Will cause the lights on the MAP to stop flashing and go steady.
When will the WARNING light illuminate?
Whenever a RED MAP light illuminates.
How many compressors are there?
2
What are the engines flat rated to?
1800SHP
Do the power levers activate the secondary low pitch stop switches?
Yes
What is the model of engine?
PW118 or A or B
What is the engine oil pump driven by ?
HP spool on the TMM accessory drive
How would you describe the combustion chamber?
Reverse flow annular combustor
What would happen if the HMU solenoid fails to de-energise descending through 14000ft.
Descending through approximately 10000ft the 10K switch triggers an EEC warning.
- 3 Chime aural alert
- EEC 1 or 1 Light
- “ENGINE CONTROL”
- WARNING lights flash
During flight, the primary low pitch stop is a function of :
The BETA valve
What are the indications of a feathered propeller?
Np approximately 20%
How long will the propeller Aux oil pump run for?
20 second timer
What is the main component responsible for controlling propeller pitch?
PCU
How is the propeller driven?
A shaft from the power turbine through to the RGB
What are the arming requirements for Auto-feather?
- Auto-feather switch ON
- PLA both greater than 62*
- Torque on both engines above 62% +- 1.4%
When is autofeather triggered?
Torque on either engine drops below 23.6 +-2.5%
How can you fill up the Aux oil tank if depleted?
Motoring the engine with the starter.
In flight Np is controlled by?
PCU and condition levers.
