DIN Flashcards
When will pressurization begin?
When the thrust is set for takeoff (levers>60*)
How do you know a door is pressurized
Red handle
For how long does the cockpit voice records?
Most recent 2 hours
Emergency equipment
4 1 /2 2 /3 3
Clases of fire and extinguisher
CLASS A(paper,wood,fabric,rubber) fire extinguisher filled with antifreeze extinguisher agent Halon extinguisher CLASS B(oil,grease,flammable liquids) CLASS C(electrical or electronic)
What components does the AC powers?
TCAS: traffic collision avoidance system
GPWAS: ground proximity warning
WINDSHEAR
If you have an overload above 500 what battery will you turn off?
Battery no. 1. why?
Under what conditions are shed buses powered while on the ground assuming shed bus knob is not in the off position?
- with GPU powering the aircraft and the shed bus switch in the AUTO or override position
- with at least one generator online and the shed bus in the override position.
- with 3 or more generators online
Visual Indications of loss of all generators (check)
ISIS
EICAS
RMUs
If you are crossfeeding fuel, what is inhibit?
Ventral transfer is inhibit, it cannot occur. Crossfeed inhibits ventral transfer.
If you get a fuel low level when I have a MEL quantity is it actual fuel low level?
Yes
When will ventral transfer occur?
4630 Lbs both wings for more than 30 seconds
46-30-30
When would you get FUEL XFER CRITICAL?
at least one wing tank quantity drops to 3131 Lbs and there is 220 LBS fuel inside the ventral tank (3131>220)
What does the FUEL LR CONFIG EICAS message means?
The ventral tank has been MEL
What happens when you use the crossfeed?
- 1 fuel pump will go off
- Xfeed valve would open
- EICAS message
Fuel low level warning how much time/fuel we have?
30 minutes/half an hour
Swing start?
If a ignition is not detected at approximately 30% RPM during the start cycle, the starter-generator is de-energized. When the APU decelerates to approximately 5%RPM, the starter is automatically re-energized for another start attempt.
Does a swing start counts like a second start attempt?
No.
Whats the procedure for stopping the APU?
Press the STOP button, monitor deceleration to 0%RPM. At 0% RPM, select the APU master knob to the OFF position.
What will the APU Shut down for automatically on the ground? In FLIGHT?
On the ground, essentially any malfunction (fire, after 10s) in flight, anything not heat related.
We are taxing and we get an APU EICAS warning message, where can we find what to do?
Immediate action items. APU fire on the ground. If you exhaust this fire protection you have to evacuate the aircraft.
What happens when you pull the fire handles?
It will shut the following: H- hydraulic SOV A- Engine bleed valve (air) L- Engine lip anti-ice valve F- Fuel SOV
Which hydraulic system control outboard/inboard spoiler? What system controls what?
SPLR INBD hydraulic SYST 1. - SPLR OUTBD hydraulic SYST 2.
[If you dont know you could see in the poster, it says in the panel]
Fire detection test.
If you do the fire detection test and you hold it for less than 2 seconds the BAGG EXTG button stays illuminated
If its necessary to repeat the test wait at least 6 seconds before pressing the test button again.
Repeat the test by pressing and holding the fire detection test button for at least 2 seconds.
If the APU is running on the ground and we hold the fire detection test for more than 10s what would happen?
The APU will shutoff automatically
What are the indications of a successful fire detection test?
-5 Messages ENG 1(2) FIRE ENG 1(2) FIREDET FAIL APU FIRE APU FIREDET FAIL BAGG SMOKE -Master warning and master caution buttons illuminated -both fire handles illuminated -BAGG EXTG button illuminated -AURAL fire bell
[APU DOESN’T ILLUMINATE]
The Accumulator allows [supplied by hydraulic syst no.2 emergency/parking brake]
At least 24 hrs of parking brake actuation
OR
6 complete emergency actuation
What is the priority valve? Only Hydraulic system no.1 incorporates a priority valve
If the system is powered by the electric motor-driven pump and the landing gear is commanded to retract, the valve will provide minimum flow to the landing gear system and give priority to the flight control services. In this case, the landing gear will operate through the accumulator pressure.
With the blend knob in the AUTO position, when will the XBLEED valve open automatically?
When an engine us being started using a pneumatic source from the other side of the system (eg. Cross bleed start, engine#2 start using APU bleed, engine#1 start using external air source)
The 14th stage high stage valve (HSV) will open automatically during:
- Low engine thrust operations
- Engine cross bleed starts
- Anti-ice operations
Regarding the priority logic of the available bleed sources, if the APU bleed was selected open, what would occur after opening the engine 1 bleed valve?
The APU bleed valve would close. Engine bleed air has priority over APU bleed air.
Pneumatic panel power sources
-Everything below the packs on the panel is Essential powered: XBLEED BLEED 1 APU BLD BLEED 2
Cockpit temperature control knob
AUTO Mode: temperature between 18/29C 65/29F
Manual Mode: no Range.
Pack distribution
Pack 1 80%flight deck 20% passenger cabin
Pack 2 20%flight deck 80% passenger cabin
Gasper fan cannot be shut off on:
The ground.
- Because it colds the rear electronics bay
- passenger outlets
- O2 cylinder compartment
When do the RAM air doors open automatically In flight?
Both packs off in flight. Doesn’t provide pressurization, only Allows ambient air.
ELEK BAY OVTEMP EICAS message
Means the forward electronic bay has reached a high temperature (70*)
Entire reference anti-ice disagree EICAS Message ENG REF A/I DISAG
Under 2 conditions: Your engine anti-ice protection system selection is not the same than the one in the takeoff data entered. And vice versa.
What does SPS/ICE SPEEDS EICAS message tells you
Presented to indicate that the ice detection/SPS interface logic is active, and consequently the SPS will actuate at reduce angle of attack values when the flaps are positioned to 9,18,22*
What differences are found in the XR anti-ice systems compared to the other EMB145?.
The 145XR upper wing surface contains DC-Powered clear ice detectors that function on the ground only. EICAS Message CLR ICE1(2)
What is the function of the dump button on the automatic pressurization controller? Will the DUMP button work if the digital controller is set to manual mode?
The dump button will de-pressurize the cabin of the aircraft to an altitude of 14500’ MSL or the actual altitude of the aircraft whichever is lower. No. The dump button will only work if is in AUTO mode.
The ice detection system
EICAS Message ICE CONDITION
60s deicing cycle is Automatically turn on.
Attitude de-clutter
During unusual attitudes, unnecessary information is removed, allowing the pilot to focus on essential information on the EADI -65 Deg bank -30 deg pitch up -20 deg pitch down Chevron will point to the horizon
Rudder hardover protection
Automatically shuts off hydraulic assistance when: -Rudder deflection above5* +- 1
- Force above 130 lbs on the pedal opposite to the rudder deflection
- Both engines running
Common comparison monitors
Amber
- ALT: Altitude differs by +-200
- HDG:heading differs by +-6
- IAS: indicated airspeed differs by 5 kts or more for longer 2 seconds
- CAS MSG: cree alerting message on one SG not the other
What does yellow needles signify?
We are using cross sided information. From a single source
When are the EICAS messages inhibit?
Above V1-15 until 400’AGL
Below 200’ RA until touchdown
System inhibition stick pusher
- On the ground (except during the test)
- below .5G
- if the quick disconnect button is kept pressed.
- below 200ft AGL. (Reverts to 10s after takeoff if the radio altimeter have fail)
- if either SPS cutout button has been pressed (released or, unlatched button position)
- above 200KIAS
- if at least one SPS channel is inoperative.
When will the stick shaker activate?
When the aircraft symbol touches the PLI
Pusher
Conectes to the speed awareness White: 1.23 Vs to 1.13 Vs Amber: 1.13 Vs Vs Red: indicates Vs (pusher) Pusher is not connected to the PLI
PLI pitch limit indicator
The PLI makes the shaker occur when the miniature airplane touches the shaker
Green: 10-5 of shaker
Amber: 5-2 of shaker
Red: less than 2 of shaker
What are icing conditions?
>10* Visible moisture Ceiling <1700' agl Visibility <1sm Ground contamination(snow, slush, water etc)
When will the stall protection test button illuminates?
If SPS has not been tested
If SPS test has failed
[We cant mel the SPS]
DAU channel failure
[DAU A (switch to B using EICAS reversionary panel)]
[DAU B(no immediate action contact mx)]
Anormal engine starts
Abort immediately when:
- N2 decreasesor remains steady for more than 30s (hung start)
- N2 indicates no rotation up to 10s after start
- no lift-off within 10s of fuel flow indication(ground)
- any unusual noise or vibration
- engine instruments indicate abnormal conditions
- flames are visible
- ITT approaches start limit
- oil pressure does not reach 34 psi after engine stabilize
Thrust reverses activation
- For activation Requires a ground signal from the main gear air/ground sensor and thrust lever at idle
- for max reverse requires a ground signal from the nose landing gear air/ground sensor or 25knts or greater main wheel speed
Powerplant
Rolls Royce turbofan engine
- High bypass ratio
- two spool axial flow turbofan engine
- single stage fan
- 14stage compressor
- 2 stage high pressure turbine to drive the compressor
- 3 stage low pressure turbine to drive the fan
- 2 full authority digital electric controls (FADEC)
- accessory gear box
- 2 bleed air taps
