ERJ Systems Flashcards
Describe the IDG (Electrical)
Each engine has an IDG monitored and control control unit (GCU). When an engine starts, the IDG will automatically come online, powering the respective AC bus. The previous power source is disconnected from the AC bus. For automatic Operation of the electrical system the IDG must be auto position. OFF- the generator line contactor opens, tripping off line and de exciting the selected IDG. When the oil pressure drops below 140 psi plus or -25 psi or the IDG oil temperature reaches 335°F plus or -10 Fahrenheit the EICAS message IDG 1 (2) OIL is displayed with an amber LED near the IDG knob on the overhead panel, this LED indicates which IDG must be disconnected and extinguishes after the IDG disconnects. Manual IDG disconnection by turning knob to the DISC position and hold it for one second. Do not hold the position for more than 3 seconds. Automatic IDG disconnection occurs when manual disconnection is not performed an IDG oil temperature reaches 366°F. In both cases the disconnection is mechanical and the flight crew cannot reconnect the IDG. MX must do it.
What bus does the IDG power?
The respective of AC bus.
What is the difference between off and DISC on either IDG selector?
Off turns associated IDG off. DISC mechanically disconnects the IDG. A reset by maintenance is required to reconnect.
The IDGs provide what type of electrical power?
AC
The OFF selection on the IDG selector mechanically disconnects it from the associated engine.
False.
Name the sources of AC power.
IDGs, APU, GPU, RAT.
Describe the APU generator. Electrical.
Before engine start, when the APU becomes available the APU generator automatically connects to the AC bus ties disconnecting the AC GPU. During the APU starting cycle, battery two is isolated from the network to power the APU start bus exclusively. In flight the APU can replace an IDG source with no operational degradation.
The APU generator automatic connects to what bus (s) ?
AC bus ties
Battery 2 is isolated from
Network for what purpose?
To power the APU start bus.
When should Crew start the APU during normal operations?
10 minutes prior to push back or as necessary for passenger, comfort
Describe the AC GPU.
Once the AC GPU is connected to the airplane and power quality requirements in voltage, amperage and frequency are with an acceptable limits an available light illuminates on the GPU button. The AC GPU has priority over the batteries to power the electrical system. Pushing the AC GPU button in connects external power to the AC bus tie, according to AC source priority. The AVAIL light extinguishers and an IN USE light illuminated.
Which bus tie does the AC GPU connect to?
AC BUS Tie
Describe when the APU is started how it affects AC GPU plugged in.
When the APU is started the system operational logic automatically isolates the GPU from the AC Bus Tie. The IN USE light extinguishes and the AVAIL illuminates on the GPU button. Before disconnecting the AC GPU from the airplane, you must push out the AC GPU push button, even with the In USE light already extinguished.
How can ground staff connect the GPU without the Pilot’s?
Ground staff can connect the GPU directly to the AC/DC GND SVC buses for ground maintenance and Flight preparation by pushing their respective button located on the front ramp panel or on the flight attendant panel on the Forward right galley. 
Described inverter. Electrical.
A static inverter, AC/DC inverter, comverts 28 V DC power from batteries to 115 V AC power to supply the standby AC bus when AC power source is not available.
What bus does inverter power?
Standby AC bus
What purpose does an inverter serve?
AC standby buss is powered from a DC buss through an inverter. So an inverter allows for this process to occur and engine starts can be done with only DC power.
Describe the RAT. Electrical.
The RAT is an AC electrical device installed in the airplane note section which converts the kinetic energy of airflow across the turbine into AC power. The electrical power produce is rated at 15 kVA, 115 V AC, 400 Hz, three phase. The RAT electrical power drives the AC motor driven pump (ACMP 3A) for primary flight control tasks. These include highlift system actuation and power for essential avionics, communication and battery charging. No altitude restriction for RAT deployment in flight. 130 kts required to ensure the RAT continues supplying AC/DC ESS busses. At speeds below this, the rat may only supply the AC essential bus, and the batteries will automatically provide electrical power to the dc ess bus, and the standby AC bus through the static inverter. As airspeed decreases, low shedding occurs and the AC EAS BUS is no longer powered.
Described the RAT electrical process.
AC power sources are not powering AC buses. Rat automatically used ploys and supplies power to the AC essential bus. DC ESS BUSES are poweres through the ESS TRU. To avoid total loss of power during this eight seconds., Batteries are used as back up to power the DC ESS buses and the STANDBY AC bus. 130 kts ensures the RAT continues supplying AC/DC ESS buses. Speed below this; The RAT may only supply the AC ESS bus, and the batteries will automatically provide electrical power to the DC ESS buses and the standby AC bus through the static inverter, AC/DC inverter. As airspeed decreases, load shedding occurs in the AC essential bus is no longer powered.
Briefly explain the purpose of the R a T.
Tomorrow fied power to the AC central blustering electrical emergency. The AC essential bus has; AC FUEL pump 2A, AMP? 3A, SF-ACE 1 FLAP CH 1 ac feed, SF-ACE 2 SLAT CH 2 ac feed.
What EICAS message would indicate that the RAT has not deployed during an electrical emergency?
AOM 2 445 warning batt discharging
What AC busses are energized during an electrical emergency before the RAT deploys? After the RAT deploys? What items are on the AC standby bus? AC essential bus? Refresh by looking on schematics AOM 2 435.
- A 2 435. Ac bus 1, ac bus 2, ac ess bus and ac stby bus.
- ac ess bus and ac stby bus.
- AC STBY BUS: ENG 1 Exciter 1A. ENG 2 Exciter 2A.
- AC ESS BUS: AC FUEL pump 2A, AMP? 3A, SF-ACE 1 FLAP CH 1 ac feed, SF-ACE 2 SLAT CH 2 ac feed.
What will cause the rat to deploy automatically? What speed is needed ensure the rat continues to provide electrical power?
- Loss of AC power.
- 130 kts.
In case of total AC power loss in flight…
The RAT should automatically deploy and provide limited AC power.
What does the AC electrical system consist of?
2 IDGs, APU, RAT, Static inverter (ac/dc inverter).
Understand the AC power priority. Outside, inside, outside, cross side.
What type of circuit breakers does that even 75 have? How do I access them?
Thermal and electronic. On the side panel and in the MCU.
What purposes and inverter serve?
AC standby bus is powered through a DC bus by inverter. So inverter allows for this process. Engine starts can be made with only DC power.
On the ground, an engine can be started without AC power.
True.
The DC electrical power consists of what?
Three transformer, rectifier units. TRUS. Two batteries.
What on the ground can be used to start the APU?
DC GPU
What are the TRUs function?
The TRUS, rated at 300 a, are used as primarily source of DC electrical system, converting AC power from the AC buses into DC power.
What is the total DC power available?
TRU 1, TRU 2, TRU 3. BATT 1, BATT 2. DC GPU.
How do you the TRUS work?
3TRUS convert 115 VAC power into 28 VDC. Each TRU works in isolation. If one of them fails, the buses are automatically powered by the remaining TRUS, as long as the DC bus ties toggle switch is selected to auto.
What does TRU one provide?
DC power to DC bus one, DC ESS bus, one, DC ground service bus, hot battery bus one and battery one charging.
What does TRU 2provide?
DC power to DC bus two, DC essential BUS 2, hot battery bus 2 and battery 2 charging.
TRU ESS provides DC power to?
DC ESS BUS 3.
What purposes does a transformer rectifier unit serve?
Convert AC power to DC power. Each works on isolation so if one feels the other is automatically picking up the load.
The TRUS convert DC to AC power
FALSE
What is the minimum voltage for battery one and battery to during this evening and power of checklist?
22.5 V.
The hot battery bus power certain items on the airplane is powered down. What items are powered select all that apply? A) pressure refuel panel. B) engine fire fighting. C) cabin overhead lighting. D, navigation lights.
A,b
How did the batteries charge?
Any AC source, including the AC, GPU and the RAT via the TRUS
Electronic circuit breakers, protect load distribution to the following systems.
- AMS
- electrical
3 fuel
4 hydraulic
5 anti-ice
6 lighting,
7 oxygen
8 engine, ignition and starting
9 water
10 APU
11 fire protection
Where are electronic circuit breakers located?
Electronic circuit breakers are located inside the SPDAs, in the electronic bays.
Where are the thermal circuit breakers located?
On the cockpit side, wall panels and others inside the ICCs in the electronic bays
How can you reach remote CBs?
The CB function key on the MCU.
What is the SBDA?
From the electrical buses, the power is directed to the airplane systems and components through the SBDA. The SBDA works as circuit breaker or relay interfacing The electrical buses with the airplane systems and components.
What is a MAU?
Airplane systems that require a complex logic for the normal operation are connected to the MAUS, which have the ability to process various inputs and define either on/off or open/close status for a specific system.
What are two main components on the DC hot that bus one and two that we as pilots care about?
Batt 1:
Courtesy/service lights at
FWD DC ceiling lights, engine one oil level indication, engine 1A fire extinguish, engine 2A fire extinguisher, engine fuel shut off valvE one, hydraulic system shut off valve one.
BATT 2
CMC, engine 1B fire extinguish, engine, two oil level indication, engine 2b fire extinguisher, engine fuel shut off valve 2, hydraulic system shut off valve 2, panel refuel three, water and waste management system controller power three.
Understand AC power priority. On side, inside, outside, cross side.
The source priority order for powering, the airplane is; Respective IDG, APU generator, GPU on the ground without a few, opposite IDG. AOM 2 401
AC BUS one and AC bus 2 determine their own AC source independently in order of on side, inside, outside, cross side.
Respective IDG: on side.
APU generator: inside
GPU without APU: outside
Opposite IDG cross side.
Electrical system abnormal operation. What happens if one AC power source fails? AOM 2 431
If one of the AC power sources failed, both AC electrical networks are automatically connected by bus tie contactors. BTCS. One AC power source of sufficient to supply the whole system, without significant degradation or additional workload. Load shed: Spda commands load shedding of Galleys and right windshield heat. When possible it restores these.
What happened with the TRU failure?
Case of a true failure, the respective DC passes automatically power connected to the DC electrical network through both essential tie contactors and DC tie contactor according to the system logic.
What happens if there’s a total loss of AC power?
The rat is automatically deployed and it powers all essential buses.
What EICAS message would indicate RAT has NOT deployed during an electrical emergency.
Aom 2 445 WARNING BATT DISCHARGING
What type of engine does the ERJ have? AOM 2 451
To wing mounted General Electric CF 34–8 E engines pretties power to the airplane. The engine is high bypass and dual rotor turban fully integrated with a nacelle and thrust reverse. The N one and into rotors are mechanically and independently operated. The engine is controlled via duel channel FADEC system, providing flexible engine operation and reduced workload. Engine indications and alert or displayed on the engine indications and crew alerting system (EICAS).
Two GE CF-34-8E5 High Bypass, 2 spool, axial flow turbo fan engines
N1= Single stage fan and 4 stage LO turbine
N2= 10 stage compressor and 2 stage HP turbine
When will engine thrust modes automatically change?
They are listed to automatically change per the AOM descriptions below for…Take off reserve (TO-1 RSV, TO-2 RSV, TO-3 RSV) and Idle. AOM 2 479-482. Look this up for a complete answer.
What is ATTCS? AOM 2 475-477
ATTCS Is controlled by the full authority, digital electronic control, FADEC. Automatic takeoff thrust control system. the ATTCS is controlled by FADEC It is available on take off and go around.
Takeoff: the ATTCS Can we slept in on our offer take off. By default it will be slapped it on. The selection is made on the MCD you take off data set menu page and the indication is displayed on the EICAS as follows: ATTCS white armed green engaged.
The engagement only happens in the thrust Lefors reach the toga set position. Around in-flight the attics is automatically armed anytime the thrust rate mode is go around, making the garage possible whenever activation criteria is met.
When will ATTCS engage? A2 pge 477
The ATTCS Automatically commands RSV whenever it is engaged, thrust levers are at TOGA, position and one of the following conditions occurs:
1. Difference between both engine N1 values is greater than 15%
2. One engine failure during takeoff
3. One engine failure during go around
4. Windshear detection
The RSV Mode is manually activated by moving the thrust levers to MAX position whenever that a TTCS is engaged. Whenever that a TTCS is activated, the green, ATT,CS indication on the EICAS disappears, and the cyan thrust mode will be displayed with an additional RSV indication. 
Engine: Recite starter limitations.
Recite engine abnormal start memory items. Also, what are the seven reasons for aborting start?
Affected engine: start/stops selector, Stop.
- No positive oil pressure indication within ? Seconds after N2 speed starts to increase.
- During engine start with a tail wind when a positive increase of N1 is not indicated before starter cut out, 50% N2. In this case, the airplane is repositioned prior to engine start to minimize tailwind effects.
- No ITT indication within 30 seconds after initiation of fuel flow (no light off)
- ITT exceeds start limit, 815°C, hot
- Oil pressure stabilizes below the engine limits.
- N1 and/or N2 failing to accelerate to stable idle speed, hunt start
- An intermittent electrical pneumatic or starter malfunction occurs before the starter disengagement
FADEC will automatically abort an engine start in the event that______
A2 483 . FADEC provides injured and start production on the ground as follows. Hung start, hot start, no light off.
When will CLB thrust be automatically set on the EICAS? CRZ? GA? RSV? AOM 2
CLB- During aircraft power up, if selected take off thrust is lower than CLB1CLB2 mode becomes a default until the next airplane power down/ power up
CRZ- Maximum N1 that can be used in cruise flight. Occurs in level out at final altitude.
GA- activated in flight when landing gear and flaps down by pressing TOGA.
RSV- takeoff- ATTCS is triggered and TO-x RSV with maximum N1 is activated.
What is the difference between T01 and TO2 thrust settings?
A2 482. TO 1 is a higher of the two thrusts available.
What is the difference between CLB one and sCLB 2 thrust settings?
CLB 1 is the higher thrust rating than CLB 2.
When FADEC automatically aborts engine start why must we still conduct the memory item?
Switch logic, protect engine wear and damage.
What learning scenario would you need thrust reverse?
Contaminated runway.
The thrust levers command the FADEC electronically. True or false.
True. Thrust levers digitally command, the FADEC, and set engine in N1.
What condition would warrant the use of MAX thrust? A. short field takeoff b the windshear escape maneuver c stall recovery.
Short field takeoff
What is the primary means to set the engine thrust? A) N1 gauge B) N2 gauge C) FADEC auto selects all thrust setting in toga detent D) itt
n1 gauge Is the primary gauge used to set thrust
ATTCS is required to be on for takeoff. True or false.
True
When the thrust reversers are open, a green REV icon appears on the EICAS between the N1 and ITT gauges. True or false.
True.
What is the first start Attempt time limitation? Engine.
90 seconds.
What is the minimum oil pressure after engine start?
Green (25 psi)
Before each flight, the engine oil is checked in, must be indicating ____to fly.
Green, not amber.
Cross bleed starts require what range of psi?
40-45.
To extend engine light, the engine stress is changed based on fees of flight. What change is this? And what phase is a flight?
Full authority digital engine control, FADEC, automatically manages a thrust mode- TO, CLB, CRZ, GA
Automatic take off thrust control system, ATTCS, is a FADEC feature that will automatically increase thrust during a takeoff or go around when thrust levers are in tea TOGA and:
-an engine failure detected, or
-N1difference between engines of 15% or more, or
- Windshear is detected
What is N1?
N1 Is the speed of the shaft with the fan, low pressure compressors, and low pressure turbines.N1 Is the primary gauge used to set thrust. 
What does a cyan chevron show on the N1 gauge?
Target N1 at TOGA thrust.
What does the green line show on the N1 gauge?
The green line shows the target N1 at MAX thrust.
Describe with the meaning of a high bypass engine is?
Since the engines are high bypass, most of the air that enters the engine is accelerated by the fan, then flows out of the engine, bypassing the core.
For normal operations what is the highest thrust use?
TOGA
When is MAX thrust use?
Stall Recoveries, windshear, escape maneuvers, or as needed for single engine operations.
What does interstage turbine temperature, ITT, measure?
Measures engine temperature, and the maximum ITT is shown by red tick mark.
What is N2?
N2 is the speed of the shaft, linking the high-pressure compressors and turbines of the engine (the core of the engine.)
Are there N1 and N2 shafts combined or separate?
The N1 and N2 shafts rotate independently and are N OT mechanically connected.
Cross bleed starts require a minimum of what psi?
40 psi. Slowly increase the thrust of the operative engine to get at least 40 psi.
What is a potential threat with FADEC on a crossbleed start?
Beware of the potential threat of FADEC swapping from 10th stage high pressure bleed air to 6th stage low pressure bleed air automatically. This could result from moving the thrust levers too quickly and too far forward. If this happens a hot start could occur.
On the ground thrust should be limited to what N1 as much as possible?
40%
What does stop on the engine selector do?
Commands the FADEC to shut down the engine. Thrust levers must be in the idle position.
What does start on the engine selector do?
Initiates engine start procedure. Fuel is automatically introduced at 20% N2 as long as the ITT is less than 120°C. Run. Normal position for engine operation.
Describe the free selections for the ignition selector knob.
- OFF: Deactivates, ignition and inhibits fuel flow on the ground. The FADEC ignores OFF inflight.
- AUTO: FADEC turns the ignition ON when Engine start attempt with at least 7% N2, one igniter. Automatic re ignition, both igniters.
- OVRD: Enables FADEC to continuously activate BOTH igniters.
What did the thrust levers do?
They digitally command, the FADEC and set engine N1. 
How does thrust reverse work?
The engines are equipped with thrust reversers, which direct bypass air sideways and slightly forward. In flight the triggers are locked down to help prevent an effort and thrust reverser deployment. 
How can we tell the thrust reversers are working?
When the thrust reversers are commanded open, and Amber REV appears on the EICAS between the N1 and ITT gauges. When the reverses are fully open, REV turns green. Reverse thrust is used on landing as needed, for example, short runway and definitely on a contaminated runway.
A 2 p 461. All the inputs required by the FADEC for the takeoff N1 computations are made through what?
T/O DATASET MENU, on MCDU
What does the engine fuel system provide?
The engine fuel system provides a fuel pressure station, filtering, heat exchange and operational, bleed valves and variable geometric actuators.
Explain how the engine fuel pump works.
Fuel supplied by the airplane fuel tanks, flows to the engine fuel pumps. Upon exiting the tanks, the fuel flows through the low pressure pump and then divides into two paths. One flows through the high pressure fuel pump and returns to the fuel tank as motor flow.
The second flows through the fuel/oil heat exchanger to the future. Once filtered, the flow leaves, the FMU and passes through the high pressure fuel pump, before returning to the FM you. 
What is the fuel/oil heat exchanger?
The fuel cooled oil cooler Maintain soil temperature within an acceptable range and heats the engine fuel to prevent freezing.
What is the fuel metering unit?
The FMU, controlled by the SADEC, meters, and distributes the proper amount of fuel for combustion to the injectors under all operating conditions. The FMU controls the shut off valve used during all normal shut downs, and provides over speed protection. AOM, volume two, page 463.
Engine. What is the variable geometry actuator?
Variable, geometry, actuator consist of two field trip and actuators controlled by the FADC via FMU. The purpose of the actuators is to optimize the position of the compressor staters as a function of corrected in to revive optimum compressor efficiency.
What are the fuel injectors?
The fuel injectors atomized the fuel from the FM you and direct it into a combustion chamber.
What is a general description of the lubrication system of the engine?
A2 465. Each engine has an independent lubrication system. The oil system lubricates and cools the turbine engine, main shaft, bearings and accessory gearbox. Oil is pressurized in a lubrication pump, and then passes through the filter, the fuel oil heat exchanger, and is then divided into several circuits to lubricate the engine. The main components are the oil tank, oil, pump, oil filter.
Describe the starting and ignition systems.
The engine starting system consist of, air, turbine, starter and starter control valve. The pneumatic system provides bleeder to the ETS to rotate the rotor, sweet and start the engine. The FADEC opens the starter control valve, providing bleeder from the APL, a ground source, or the opposite engine. The AirTrain starter is a turbine that it’s smaller is the engine to a self-sustaining RPM level. The FADEC closes the SCV with us or cut up speed is reach. A2 467.
Ignition system. The ignition system provides an electrical spark for the fuel combustion during ground, in-flight, start attempts, and for automatic relate. The FATEC energizes one igniter for on ground engine starts, and both igniter is for inflate engine starts. When the ignition selector knob is placed on the override position, both igniters on each engine or energize.
Starter operation, the engine starter is controlled via the engine start selector knob on the power plant control panel. Four on ground starts the SCV opens providing leader to the ATF stand crease, rotor, speed for engine start. 
Describe generally the engine control system.
The engine control system, performs, engine, control and thrust management, provides information to the carpet, maintenance reporting an engine condition monitoring. The engine control system consist of the feedback, fresh liver, T2, and anyone sensors. The FADEC uses input from the airplane and engine to monitor and manage the engine control system. The thrust lever receives inputs of the desire trust from the pilots or from the auto throttle. The tea to censor monitors engine, inlet air temperature for use in FADEC control calculations. The end one sensor provide fan speed data for the FA DEC, an airplane vibration monitoring system.
Describe FADEC.
The FADC is the main component of the engine control system. It’s functions include, engine, protection, control of the requested, and max in one, control of the Att CS. The FDC has to it in a cold, but isolated channels. One operates as the Incontrol channel and the other as a standby. The standby channel constantly processes all the data, and is always ready to take control of the engine in case the actor channel fails. The FADC in control channel switched on every inch of her.
Engine thrust ratings. AOM, volume two page 477.
The FDC calculates the maximum and one for each thrust rate mode adjusted for attitude, temperature and airspeed, and displays both digital and analogical readings on the N1 indicator. The thrust rate modes of the following. Take off, take off one take off to take off three. Take off reserve, take off one reserve, take off to reserve, take off three reserve. Go around. Go around reserve. Maximum continuous stress. Maximum climb, climb, one, climb too. Maximum cruise CRZ. Idle.
AOM to page 481. Describe FADEC, engine protection.
The FAADEC provides interest her protection on the ground as follows, hung start, hot start, no light off. Over speed protection, whenever they’re into reaches 102% the FADEC automatically commands an engine shut down. In the event of three consecutive over speed detection events within 30 seconds the FADC will not relate the engine. Over temperature protection, the FAADEC controls the ITT limits for engine start and throughout engine operation. ATT limit is very little according to the engine operation phase. ITT over limit protection, during engine start if the Att reaches its limit the FADEC automatically shuts off if your flow aborting the start sequence. In this case, the start control valve is not automatically close. Pilot intervention is needed to close SCV by selecting a start stop switch to stop. Engine start, HIIT prevention, temp route to Att control the engine ground starts to FADEC will not allow fuel flow if Att is above 100 and Drew 20°C. In this case, when the pilot sets the start stops left her to start the shower control valve is committed open but the fuel flow only starts when Att drops below 120°C. 
What are the areas of the aircraft that have fire protection? Hey. Engines V. Lavatory, trash, cans. See Carl compartments de Main passenger cabin. EAP you. Select all that apply.
The fire protection system provides fire detection and extinguishing for what
Engines, a few, cargo, compartments, lavatories. In addition, portable fire extinguishers are located in the cockpit in cabin.
An event of a fire protection system component failure what will you see
I cast caution message will be displayed and fire on that system can no longer be detected
If a fired is detected. What happens
EICAS warning message will appear. The appropriate handle/button will illuminate. Master warning light will slash. triple chime in fire bell will sound.
Is inch and one fire is detected. What happens
The handle lights up. When pulled three valves close. Fuel shut off valves, hydraulic shut off valve
How many engine fire sting wishing bottles are there?
There are 2 inch and fire extinguishing bottles. Bottle and bottle be. Both can be used in one engine or one in each. We can discharge the Helen bottles into the engines to fight in the engine fire, even when the aircraft is powered down.
When the engine fire extinguishing bottle is discharged siren handle illumination______
May be lost. In this case, if the CAS message is still active the fire condition persists.
If a fire is detected in the Ford cargo bin, what visual overhead panel do you have?
Ford cargo button illuminates red.
When the Ford cargo button illuminates read what happens
The air circulation fan is turned off. Heirate fire extinguishing bottle is armed. The Ford cargo compartment ventilation outflow valve is commanded close.
When the Ford cargo extinguisher button is pressed, what happens?
It’s a Sturgis, both the high and low rate Halo on fire extinguishers (in flight. When button is illuminated.)
If the Ford cargo button is not illuminated, what do you have to do?
Press to arm, press to discharge.
On the ground, pressing the Ford cargo fire extinguisher button once does what?
If the light has an illuminated, and it is armed, or if you have pressed it, wants to arm it, because the light did not come on… On the ground one press only the high rate Halen bottle discharges. It will require an additional trust to discharge a little rate, hairline bottle. So it would take three fast as a discharge, both bottles if the button didn’t initially illuminate on the ground.
There are—- Hey lawn fire extinguisher bottle shared between the forward and aft cargo base. Can they be used to fight a fire in Beaufort and aft? 
Two. They can be used to fight a fire in either the Ford or ass, but not both.
Press and hold the fire detection system test button to test what?
Smoke, engine, and a few fire detection systems.
Holding the fire detection system, test button does what?
Test all fire button/handles illuminate red. Master, warning, light illuminates. triple chime, and fire bell oral warning sound. 5E I,CAS fire messages appear.ENG 1, ENG 2, APU, CARGO AFT, CARGO FWD. FIRE Illuminate inside both the Att gauges. 
What button illuminates is fire detected in the aft cargo van?
Aft, cargo illuminates read in the high rate. Fire extinguisher bottle is armed. It is the same issue with arming and deploying as the four cargo bin.
What button illuminates if an APU fires detected?
AP fasting shirt button. If the EM ER stop push button is not pressed, the APU fire extinguisher light will illuminate one minute after the fires detected.
If you fire extinguisher button is illuminated, and the EMER stop but push button is pressed. When press what happens?
If you feel shut off valve closes, if you Halen, fire extinguisher, discharges, turns off the red striped bar on the APUEMER stop push button.
APU emergency stop button, what are the colors?
The top half illuminates, right of the APU far is detected. The bottom, half illuminates white when pressed.
The APU feels shut off valve, will automatically close if a fire has been detected for___while on the ground only.
10 seconds. This will also have another fire extinguisher test button is pressed for 10 seconds for a longer.
Fire protection, system provides EICAS messages for
Engines, APU, cargo, compartments, lavatories. The laboratories have smoke detectors and fire extinguishers built into the trash cans. If the trashcan reaches a certain temperature, Halen is automatically discharge.
If smoke is a text, Anita lavatory what happens?
The master warning, lights illuminate. The EICAS warning message LAV smoke is displayed. In the laboratory with a smoke has been detected. An alarm sounds and a smoke detector. Light comes on. A flashing orange light on the respective attendant lights, panel, rainbow lights, illuminates.
