Embraer 505 Question Bank Flashcards
What engines are on the Phenom 300?
How many lbs of thrust?
Pratt & Whitney PW535E; 3360 lbs of thrust
How are the engines controlled?
By a dual channel Full Authority Digital Electronic Control (FADEC) system. Each engine is controlled and monitored by two FADEC channels. When one channel is in control, the other is in standby mode.
What supplies power to the FADEC?
A 28VDC airframe power is required to enable operations of the control system and power to start the engine. Once the engine is running, the FADEC takes its primary power from either the engine PMA or the 28VDC airframe power, whichever provides more power. The 28VDC airframe power bus is available for back-up supply purposes.
What are some of the functions of the FADEC?
- During Battery START, it accelerates the operating engine’s N2 to 72% to protect the gear box from damage.
- Ensures no limits are exceeded on hot, hung or no start.
- Controls Automatic Thrust, (ATR).
- Provides WHSAIS envelope information to the AMS controller.
- Schedules fuel flow during starting based on N2 speed and ambient conditions. * Controls the igniters.
- Calculates an N1 speed setting corresponding to the Thrust Lever Angle, (TLA) position selected, and compensates this setting for ambient temperatures and pressures, aircraft bleed off-takeoffs and operating modes. The FADEC then governs the engine to this N1 value.
During start, when are both igniters automatically energized?
The FADEC energizes one igniter for ground engine starting when
TT0 is above 0°C and both igniters when TT0 is below 0°C or for in-flight engine starting.
How does the FADEC assist an In-Flight Start?
FADEC automatically actuates both igniters during starting and disables the abort starting logic. In this case, the decision on whether to abort an unsuccessful start is at the pilot’s discretion.
How does the FADEC assist for an Auto Relight?
The FADEC continuously monitors the engine parameters and automatically turns on both igniters and schedules the relight fuel flow in case an engine flameout is detected, assuming the ENG START/STOP knob is out of the STOP position.
How is dry motoring performed?
By setting the ENG IGNITION switch to OFF, while the engine is in shutdown state, and by setting the ENG START/STOP knob to START.
What is the purpose of the Permanent Magnetic Alternator, (PMA)?
The PMA is the primary source of AC power to both channels
of the FADEC when the engine is running above idle. Below this speed, the primary source of AC power to the FADEC is the airframe 28VDC power, which is used during engine starting and as a backup source for the PMA.
What is the purpose of the ATR?
The ATR, controlled by the FADEC, automatically provides maximum engine thrust (TO RSV or GA RSV) whenever it is armed, and one of following conditions occurs:
TLA at TOGA
What will happen if the START/STOP knob is moved to STOP and the TLA is not at idle?
The FADEC will disregard the STOP selection and not shut down the engine.
Under normal operating conditions what color are the engine instruments pointers and digits?
Green.
What does an “E1/2 OIL IMP BYP” CAS message indicate?
There is an impending blockage of an oil filter.
How many batteries power the airplane?
Two.
What type are the batteries?
Lead-Acid.
Where are the batteries located?
1 in the nose; #2 behind rt. wing root.
How many volts and amps for each battery?
24VDC; Batt 1 34 A, Batt 2 48A
Which battery provides electrical power for engine starting?
2 battery
What is the minimum voltage for starting? Charging?
24V and 27V
How many generators? Volts? Amps?
Two. 28VDC. 400A.
What are the generator loads?
Ground: 330A
Flight: 390A
What is the minimum battery temperature for normal operation?
-10C
What function in the electrical system allows the engine to start without causing surges in the Avionics?
Quiet Start Contactor
If a single generator fails in-flight, what happens?
Both SHED BUSES lose power.
What does it mean if the GPU is plugged in, but there is no GPU AVAIL light illuminated on the button?
DC power requirement from the GPU of between 25V and 30V is not being met.
What are we looking for when we push in the Electrical Emergency Button on the before taxi checklist?
That the batteries show at least 23.5 volts.
(The generators continue to power the DC busses in this scenario, but certain other relays open in order to confirm battery voltage).
If the GPU is powering the airplane, when do the generators come on line?
When the GPU is disconnected (from the Central Bus) which can be confirmed on the electrical synoptic page.
If the GPU is connected and the Electrical Emergency Button is pushed in, what happens?
Because the generators are not on-line yet, the electrical system is forced into electrical emergency, connecting the batteries directly to the emergency buss.
(The GLC 1, GLC 2, SBC 1 and SBC 2 will be commanded to open, and BTC 1 and BTC 2 will be hardwire locked out, EBC 1 will open and EBC 2 will close).
The Batteries 1 and 2 will supply power to the HOT BATT BUSES, EMERGENCY BUS and the CENTRAL BUS.
If a Dual Generator failure occurs in flight, what remains powered?
The aircraft wiring logic will automatically configure the electrical emergency scenario. The Batteries 1 and 2 will supply power to the HOT BATT BUSES, EMERGENCY BUS and the CENTRAL BUS providing engine starting.
For approximately how long will the battery supply power following a dual generator failure?
45 minutes max?
If while in flight, the CAS message ELEC XFR FAIL appears, what is the memory item and why is this procedure necessary?
ELEC EMER BUTTON…………PUSH IN
A complete in-flight loss of the main generating system has occurred, but the automatic transfer logic has failed to configure the electrical emergency condition, so pushing in the button allows the pilot to override the automatic transfer failure and enable the load shedding process by forcing the system into the electrical emergency condition.
What is normally powered by Starter Generator 1?
DC BUS 1, SHED BUS 1, EMERGENCY BUS and HOT BATT BUS 1.
What is normally powered by Starter Generator 2?
DC BUS 2, SHED BUS 2, CENTRAL BUS, HOT BATT BUS 2.
Where is the fuel stored?
Two integral wing tanks.
How many pumps are found in each tank and what are they called?
Three; one ejector pump, one scavenge ejector pump, one electric fuel boost pump.
What is normally used to supply fuel from the wing to the engine fuel control unit in flight?
Ejector pumps.
What is normally used to supply fuel from the wing to the engine fuel control unit in flight?
Ejector pumps.
How is the primary fuel ejector pump powered?
Motive flow from the respective engine.
What is the primary purpose of the scavenge jet pump?
Maintains the fuel level in the collector tank ensuring a constant flow of fuel to the engine during normal flight.
When is the electric fuel pump activated if in the auto position?
Engine start, crossfeed operation, if primary ejector pump fails.
What ensures that the differential pressure between the tank and ambient remains within structural limits and prevents fuel spillage?
A vent system including a NACA air inlet/outlet.
How is crossfeeding performed?
Select the XFEED switch to the wing tank with the low fuel quantity
(LO 1 or LO 2). This opens the XFEED valve and turns on the electric DC pump in the wing tank with the highest level of fuel. Both engines will utilize fuel from that tank.
What is the restriction on crossfeed operation?
Shall not be performed during takeoff and landing.
When fuel becomes balanced and the XFEED valve is still open, what CAS message will be annunciated?
“FUEL EQUAL”.
Will the total tank quantity indication be lost if only one wing tank quantity indicator fails?
Yes.
The fuel shutoff valves are normally open. What is the only way to close one of these valves?
By pushing the fire shutoff pushbutton.
What would cause a “FUEL LO LEVEL” CAS message?
310 lbs of fuel remaining in the respective tank.
What would cause a “FUEL IMBALANCE” CAS message?
220 lbs imbalance.
Is there de-fueling capability?
Yes, by means of a dump valve located under each wing.
While fueling, what monitors the fuel quantity in the tanks and controls refueling flow into each tank?
EFCU, Electronic Fuel Control Unit.
How long is maximum refueling time from empty to full?
Less than 12 min, at 50 psig.
Explain the two critical tests that should be accomplished on the control panel before re-fueling begins?
Lamp Test – When the LAMP TEST switch is held up, the LH TANK and RH TANK indicator lights stay on or come on according to the status of these lights, the FAIL indicator light turns on and the digits light up.
Shut-Off Test – When the SHUT-OFF TEST switch is held up during pressure refueling operation, the LH TANK and RH TANK indicator lights must come on, indicating that the shut-off valve closes, and the FAIL indicator light must be off.
What action is necessary to accomplish on the refueling panel if external power is not being utilized?
The POWER SWITCH must be selected to BATT.
What systems require hydraulic pressure?
Landing Gear, Wheel Brakes, Pusher, Rudder Boost, Spoiler/Speed Brakes.
What provides hydraulic variable flow and pressure to the system? And at what rate?
Two engine-driven hydraulic pumps at 3000psi (located on the accessory gear box of each engine).
In case of a hydraulic pump malfunction, what prevents rotation without interfering with the continued operation of the engine?
The hydraulic pump connecting shaft to the AGB has a recess designed to work as shaft shear point if the torque imposed by the hydraulic pump to the AGB exceeds limits.
What is the function of the Priority Valve?
It guarantees hydraulic power to the spoilers, stick pusher, rudder spring actuator or brakes by restricting the flow to the landing gear, if being used simultaneously.
What encases the hydraulic fluid? How much can it hold?
A (spring-biased bootstrap diaphragm type) reservoir. (50psi reservoir pressure, 3000psi system pressure).
Maximum 1.3 gals or 5.01L
What provides contamination protection for the fuel system?
Two disposable filter elements located on the lower portion of the manifold (one for low pressure return and one for the high pressure line; the filter can capture any particle greater than 5 microns).
What would happen if the filter fails or is blocked by too much contamination?
A bypass valve will open to allow continued flow though the hydraulic system.
What is available to indicate that the fuel filters need to be replaced?
The filters have red “pop-up” differential pressure indicators to provide a visual indication when the filters need to be replaced.
How are the Fire Shutoff Valves closed?
Manually by the engine fire extinguisher shutoff buttons, automatically in case of hydraulic system high temperature, or through the shutoff switches on the hydraulic panel.
