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SV Flashcards

MG

1
Q

What’s the purpose of the safety check?

A

Short answer: makes sure switches are in the right place before you fly a new airplane. Making sure airplane is in the correct configuration before plugging in power.

FOM:
The safety check is completed prior to the application of electrical power and prior to the flight crew’s first flight of the day in each airplane they are dispatched. If accepting an airplane that is powered, verify compliance with the safety check.

WARNING:
PERSONAL INJURY MAY RESULT IF CERTAIN CONTROLS OR SWITCHES ARE IN THE WRONG POSITION AND POWER IS APPLIED TO THE AIRPLANE. IF CERTAIN CONTROLS AND SWITCHES ARE NOT IN AGREEMENT WITH THE POSITION INDICATED ON THE SAFETY CHECK (E.G., LANDING GEAR LEVER POSITION), CONTACT MAINTENANCE TO CLARIFY AIRPLANE STATUS.

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2
Q

What are the 3 read and do checklists?

A

Safety Check: checking airplane configuration before powering on

Power On Check: establish electrical power on an un-powered airplane. or verify in compliance

Securing Check:

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3
Q

Power-Up Check

A

The power-up check is performed prior to the flight crew’s first flight of the day in each airplane they are dispatched and to establish electrical power on an un-powered airplane. If electrical power is already established, verify compliance with all items.

Powering up the ERJ 170 correctly is critical for a successful power up. Follow each step as described without exception. DO NOT rush the power-up procedure.

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4
Q

Securing Check

A

When the airplane is terminating and all systems are to be shut down, the PIC is responsible for completing the securing check. The PIC may delegate the check to the SIC. The securing check is also completed anytime a power down procedure is required.

The securing check is a silent “read and do” check.

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5
Q

What are the Prior to Being Seated Items?

A
  1. Maintenance logbook
  2. Cockpit reinforced door pannel
  3. Airplane Manuals & Documents
  4. Emergency Equipment
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6
Q

In the Prior to being seated items check, what Manuals and Documents are you checking?

A
  1. Maintenance Logbook
  2. Airworthiness Certificate
  3. Registration
  4. Radio Station Certificate
  5. QRH
  6. CAT II Placard

For the complete list of required documents that need to be on board the aircraft refer to FOM 6-11.2 Required Aircraft Documents Tables.

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7
Q

In the Prior to being seated items check, what emergency equipment are you checking?

A 
PBE (Protective breathing equipment)
Fire extinguisher
Crash axe
Life Vests (3)
Escape Ropes (2)
Flashlights (2)
Spare headset (1)
Fire Retardant Gloves (1 pair)
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8
Q

Whats the first thing you check when you get to the airplane?

A

Maintenance Logs
3 check, 3 verifies,3 blank pages

  1. At least 3 unused AML pages.
  2. AMLs contain at least 1 airworthiness release
  3. No open write-ups (PIC need only check since the last Airworthiness Release)
  4. Verify the AML contains a record of required scheduled Maintenance inspections performed within the required time.
  5. Verify that all active DMIs (Deferred Maintenance Items) are within their expiration period and all procedures have been complied with.
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9
Q

How long is service check good for?

A

The Service Check is valid for two (UTC) calendar days after it is completed. A routine check may be substituted for a Service Check.

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10
Q

Maximum Operating Altitude?

A

41,000’
This is a design altitude limit and is not attainable under most operating conditions. In the AOM flight planning tables, the Maximum and Optimum Altitude table contains the actual operating cruise altitude limits.

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11
Q

Maximum Altitude Takeoff and Landing

A

8,000’

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12
Q

Maximum Runway Slope

A

+/- 2%

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13
Q

Maximum Tailwind Takeoff and Landing

A

10 knots

When computing crosswind and tailwind component, consider the entire gust factor of the reported wind (e.g. if the wind is 21010G20KT, use 21020KT as the wind for the computation) (CPS)

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14
Q

Maximum crosswind for takeoff and landing for Compacted Snow

A

20 knots

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15
Q

Maximum Taxi Speed Straight Dry/Wet?

Maximum Taxi Speed Straight CONTAMINATED?

A

30 knots

15 knots

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16
Q

Minimum airspeed for RAT?

A

130 KIAS

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17
Q

When we push the DVDR TEST button what are we looking for?

A

Push DVDR TEST for three seconds and release. Observe there are no FAIL messages on the EICAS to confirm a successful test.

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18
Q

How many minutes of cockpit audio can the DVDR record?

A

120 Minutes of audio and Digital Communication Messages

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19
Q

How many hours of flight data information can the DVDR record?

A

25 hours of Flight Data information

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20
Q

When does the DVDR start recording?

A

The Digital Voice Data Recorder Systems begin recording automatically. The Cockpit Voice Data recorder begins as soon
as power is applied, and stops when power is removed from the unit. The Flight Data record function starts when the
engines are turned on, or when the aircraft is in the air (no “Weight On Wheels” (WOW is false)). It stops when the aircraft
is Weight On Wheels and both engines are turned off. The DVDR unit is internally time synchronized for direct correlation of
the recorded Cockpit Voice to Flight Data Information. Additional Greenwich Mean Time information is provided for absolute
time marks. In the event of a fault or failure of the DVDR System, an advisory message on the EICAS comes on. Some
DVDR CAS messages will be inhibited during critical phases of flight.

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21
Q

The Digital Voice Data Recorder System has the following components:

A

Two identical Digital Voice Data Recorder units;
DVDR 1 is installed in the forward E Bay, DVDR 2 is installed in the aft E Bay. Two Impact Switches, one each mounted in
to its respective Digital Voice Data Recorder. One Tri-axial Accelerometer, installed in the left hand side wing-stub area.
One DVDR Control Panel, located in the cockpit on the overhead panel. One Cockpit Area Microphone, mounted on the
frame between both windshields.
The Digital Voice Data Recorder Control Panel uses standard input/output interfaces for a Cockpit Voice Recorder and a
Flight Data Recorder. The Test button (DVDR TEST) is used to initiate a Cockpit Voice Recorder and Flight Data Recorder
test within both DVDRs simultaneously. You can switch the FWD/AFT Switch position to check the test status for either
DVDR 1 – switched to FWD, or DVDR 2 – switched to AFT

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22
Q

What does CVR ERASE do?

A

The CVR ERASE button initiates the Cockpit Voice Recorder
Erase Function. For this function the Aircraft has to be on the ground and the parking brake has to be set. A HEADPHONE
jack is avaiable for audio monitoring. The position of the FWD/AFT Switch also determines the CVR audio monitor source -
forward or aft DVDR. The Cockpit Area Microphone (CAM) picks up area audio and delivers it to the preamplifier of the
DVDR Control Panel.

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23
Q

What buttons don’t light when ANNUNCIATIONS TEST is pressed?

A

Only the EMRG/PRKG BRAKE light, GPU pushbutton light, and fire test lights are not illuminated.

The striped bars and caption indications in all main panel, overhead panel, and control pedestal pushbuttons illuminate when pressed, allowing verification of lamp integrity.

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24
Q

Minimum battery voltage to start the APU…

A

21v

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25
Q

Battery voltage must be at or above _____ prior to takeoff.

A

22v

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26
Q

The minimum battery temperature for an APU start.

A

-20°C

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27
Q

Start environment, The minimum Air Temperature for APU start

A

-54°C

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28
Q

When stopped at the gate:

Accomplish the following flow pattern:

A
  1. SET the EMER/PARKING BRAKE.
    •Verify the EMERG/PRKG BRAKE
    indicator shows ON.
  2. Place the STERILE, NO ELECT
    DEVICES and FSTN BELTS switches to
    OFF
  3. Place both thrust levers to IDLE.
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29
Q

To avoid power transfer interruptions when connecting or disconnecting an electrical source (CPS).

A

Confirm power transfer on the Electrical Synoptic page or wait 10 seconds.

Examples of power transfers:
• Confirm power transfer on the Electrical Synoptic page or wait 10 seconds before stopping the APU after engine start.
• Confirm power transfer on the Electrical Synoptic page or wait 10 seconds after the GPU switch is pushed in or the APU power is available before shutting down the engine(s).
• After an engine shutdown and below 30% N2, confirm power transfer on the Electrical Synoptic page or wait 10 seconds before starting the APU. (Refer to AOM I, 2-12.3 APU Start Up During Engine Operation (CPS).

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30
Q

What is an IDG and how many do we have?

A

We have two engine-driven Integrated Drive Generators

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31
Q

What does an IDG do?

A

The Integrated-Drive Generators (IDGs) are the main AC power sources when the engines are running. They are mounted on each main engine gearbox. A hydro-mechanical Constant-Speed-Drive (CSD) converts variable engine speed into constant generator speed. Each IDG generates constant frequency AC power at 40kVA, 115 V, 400 Hz, 3-phase. The IDG oil system is air-cooled. The IDGs are monitored and controlled by the Generator Control Units (GCUs).

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32
Q

How many Generators does the airplane have?

A

two engine-driven Integrated Drive Generators (IDGs), one Auxiliary Power Unit Generator, one Ram Air Turbine Generator (RAT) and one AC external power input

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33
Q

What does amber light next to IDG mean?

A

An amber LED illuminates beside the associated selector knob to indicate which IDG has failed.

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34
Q

*Takeoff with ECS off, anti ice on all do you need APU on for that takeoff?

A

no you don’t need APU on.

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35
Q

How long hold the disconnect switch for IDG?

A

By selecting the knob to the DISC position, and holding it in this position for one (marty gouge says 2) second, the IDG will be mechanically disconnect.

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36
Q

Can we reconnect IDG after disconnect?

A

Only authorized maintenance personnel on ground can reset a disconnected IDG. For safety, the IDG features an input shaft shear section and a thermal disconnect operation. This will disconnect the IDG permanently if there is no manual disconnection.

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37
Q

What does AVAIL light on GPU mean?

A

AVAIL will illuminate with the button pushed in or out when the AC GPU is connected to the aircraft, but is not powering the AC BUS TIE.

IN USE Light: IN USE will only illuminate when the button is pushed in, and the AC GPU is powering the AC BUS TIE.

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38
Q

Whats the priority for the AC buses?

What is the AC electrical system‘s priority?

A 
• Onside (IDG)
• Inside (APU)
• Outside (GPU)
• Cross-Side (Other IDG)
Note: The airplane uses an onboard AC power source before an external AC source
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39
Q

What is a TRU?

A 
Transformer Rectifier Units, we have 
3 TRUs (Transformer Rectifier Units) - 28VDC, 300A
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40
Q

Whats does a TRU do?

A
  • Primary DC power source
  • Converts 115VAC into 28VDC
  • Each works in isolation from the other

TRU1 is located inside the Left Integrated Control Centers, TRU2 is inside the right integrated control center and TRU essential is inside the Emergency Integrated Control Center. DC power is generated by conversion of AC to DC power. The input of each TRU is 115V AC, 400Hz frequency stabilized, and the output is 28V DC, rated at 300 Amps of current. The TRU TOGGLE switches on the cockpit overhead panel provide control of the three transformer unit contactors, and must be in AUTO position during normal (automatic) operation. If a switch is set to “OFF”, the respective TRU contactor will open.

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41
Q

If I start APU do I need both batteries on? Why???????? Check answer not sure,

A

APU starting may use either the onboard battery 2, or power from a DC external ground cart. APU start bus is connect to Battery 2

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42
Q

What else can power APU starter motor?

A

DC external ground cart.

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43
Q

On the power up check, says 22v minimum why do we need 22?

A

(that’s the minimum for takeoff)
21v to start APU

To read battery voltage, the GPU pushbutton must be disconnected (pushed out).

44
Q

What if you have less than 21v before starting APU?

A

If battery voltage is below 21 volts, notify maintenance.

45
Q

If your power is between 21-22v what do you do?

A

Charge the batteries

46
Q

How do you charge the batteries?

A

Procedure in the AOM 1

If battery voltage is between 21 and 22 volts, use the battery charging procedure below to ensure battery voltage is at or above 22V prior to takeoff.
a. Battery charging procedure:
• Recharge the batteries prior to takeoff through any AC source including engines or GPU. Recharging using the engines during taxi may also be credited towards the charge times listed below:

47
Q

How much time will 22v of battery power give me?

A

• Will provide 10 minutes of power during an electrical emergency

48
Q

At what voltage does the battery relays drop out?

A

18v is the minimum battery voltage to close the battery bus-ties

49
Q

What causes the rat to deploy?

A

Loss of power to the AC buses.
Manually by pilot.

If there is a sudden loss of AC power In flight, the RAT is automatically deployed into the air stream. The kinetic energy of airflow across the turbine is converted into mechanical power to drive the generator

50
Q

What happens if a power-generating source fails?

A

• Bus ties automatically connect to provide no system degradation.

51
Q

How long for RAT to deploy? Why?

A

Whenever AC power sources are not powering AC buses, the RAT is automatically deployed, and after 8 s, supplies power to the AC ESS BUS. Once deployed it will create a very loud noise due to the high rotation speed, and cannot be stowed back in flight, even if normal electrical power is reestablished.

52
Q

What supplies power during the 8 second RAT deployment?

A

Batteries supply power to the DC ESS BUSSES and AC STANDBY BUS

53
Q

What is system is essential on the AC system that when rat is deployed?

A

Hydraulics (source? marty’s gouge)

54
Q

What is the minimum speed for RAT in the QRH?

A

150 KIAS

55
Q

What happens if you go below 130 KIAS with the rat out?

A

At speeds 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 and the AC ESS BUS is no longer powered.

56
Q

What does the RAT power?

A

AC/DC ESS BUSES

57
Q

Whats powered while you’re on the batteries, equipment?

A

Eiss,clock, acps, mcd 2, compass light, guidance panel, ccu, revisionary panels. (Check source marty’s gouge)

58
Q

When do I have fire protection?

A

Battery power with DC ess bus

The electrical power is supplied by:
– Engine fire detection:
MAU 1 (DC ESS BUS 1) and MAU 3 (DC ESS BUS 2).
– Engine fire extinguishing:
HOT BATT BUS 1 and HOT BATT BUS 2
59
Q

What bus powers and protects the APU?

A

DC ess bus

60
Q

When does the battery discharging horn come on?

A

On ground, if the airplane is powered only by the batteries for more than 5 min, a horn will sound to alert the ground personnel.

61
Q

What happens when I pull the fire handle?

A

Anytime the fire handle is pulled it commands the following shutoff valves to close:
– the engine fuel shutoff valve;
– the engine hydraulic shutoff valves and;
– the engine bleed air shutoff valve.
Each fire handle is associated with one engine.

62
Q

How many fire bottles are there?

A

2 eng 1 apu 2 cargo

63
Q

How many Engine fire bottles

A

A total of two fire extinguisher bottles named A and B are installed in the airplane to serve either or both engines.

64
Q

APU FIRE EXTINGUISHER BUTTON (GUARDED)

A

Momentary action pushbutton:

– Closes the APU fuel shutoff valve and discharges the APU fire extinguisher bottle.

65
Q

The Cargo Fire Extinguishing System is comprised of:

A

– One high-rate extinguisher bottle and;
– One low-rate extinguisher bottle.
Both extinguisher bottles are installed in the center avionics bay and used in either forward or aft cargo compartment.

66
Q

On the ground with apu fire whats my indication?

A

EICAS: APU FIRE
Switch is illuminated

In the event of fire, one minute has passed without the MAU receiving a positive indication that the APU Emergency Stop button was pressed, the APU fire extinguish button will illuminate. If there is an APU fire on ground, the APU will shut down automatically after ten seconds if there is no commanded shutdown through the APU Emergency Stop button.

67
Q

Following a normal shutdown sequence, When does APU SHUTTING DOWN disappear from the EICAS?

A

During a normal shutdown sequence, the APU pneumatic power is removed immediately and the electrical power is removed at the end of a 2 minutes cooldown period. The EICAS message APU SHUTTING DOWN disappears at the end of that period.

68
Q

When does the fire bottle fire for the apu?

A

Automatically on the ground, In flight after the button is pressed

69
Q

What do I do if I have a fire on apu in flight?

A

QRC

70
Q

What will the apu shutdown for on the ground?

A

The APU Fire Detection System is comprised of two detectors loops.
When a fire condition is detected the signal goes to the MAU which generates the associated EICAS messages and alarms.

71
Q

Cargo fire on the ground what do I do?

A

Push the cargo fire button

– the high-rate fire-extinguishing bottle to discharge immediately into the selected cargo compartment.
– the EICAS ADVISORY message CRG FIREX HI DISCH to display.

One minute later, the second fire-extinguishing bottle discharges automatically at a reduced flow rate and the agent remains in the selected cargo compartment for 75 minutes for airplanes with 60-minute diversion time allowed.
NOTE: –
–
Pressing the associated pushbutton before the one-minute period immediately discharges the low-rate extinguishing bottle.
In case of fire on ground, the low-rate fire-extinguishing bottle is not automatically discharged. The flight crew must push the cargo fire-extinguishing pushbutton once again to discharge the low-rate bottle.

72
Q

In the forward cargo compartment, what happens automatically when it detects a fire?

A

– Air circulation fan is turned off;
– The high-rate fire extinguishing bottle is armed and;
– The forward cargo compartment ventilation outflow valve is commanded closed.

73
Q

In the aft cargo compartment, what happens automatically when it detects a fire?

A

– The high-rate fire extinguishing bottle is armed.

74
Q

What is the first step of the fire panel test?

A

Check for no FIRE FAIL msgs on the EICAS

75
Q

When you push the fire test button what lights come on?

A

The master WARNING lights flash.
– The fire extinguisher handles illuminate steady.
– The cargo fire-extinguishing buttons illuminate steady.
– The APU fire-extinguishing button and the upper half of the APU emergency stop button to illuminate.

76
Q

Can we test the fire panel with the APU running?

A

Yes, Press and hold the test button on the overhead panel for a minimum of 3 seconds, but no more than
10 seconds if the APU is running or it will automatically shut down the APU.

77
Q

Maximum usable fuel

A

20,785 lbs

78
Q

Maximum fuel imbalance in flight

A

794 lbs.

79
Q

When do I get EICAS msg for fuel imbalance?

A

Lateral fuel imbalances exceeding 360 kg (800 lbs) are annunciated on the EICAS by the message “FUEL IMBALANCE”. This message will disappear when the difference is reduced to 45 kg (100 lbs) and the advisory message FUEL EQUAL-XFEED OPEN will appear indicating to the pilot to select the XFEED switch to OFF.”

80
Q

Minimum fuel tank temperature?

A

-40 C

81
Q

Where is the fuel temperature temperature taken from ?

A

A fuel temperature sensor is installed in the left tank only. If the temperature in the left tank drops below a pre determined value, a “FUEL TANK LO TEMP” caution appears on the EICAS. The fuel temperature can be monitored on the fuel system synoptic page.

82
Q

What can’t be on for takeoff and landings?

A

Crossfeed

83
Q

What is the collector tank for?

A

to ensure continuous fuel feed to the engine throughout the whole flight envelope. The arrangement of the tanks permits the fuel to flow from the outer tank area to the wing root, and into the collector tank. Each tank contains baffle and flapper check valves that prevent fuel from escaping from the collector tank and prevents fuel from entering the surge tank.

84
Q

What pumps are in the collector tank?

A

ejector pumps, which are driven by high-pressure motive fuel flow supplied by the dedicated engine fuel pumps

85
Q

Whats the DC fuel pump used for?

A

Apu start
and eng start if AC power not available

• Installed only in the right wing
• Provides pressurized fuel for normal APU start when AC power or the AC fuel pump 2 is not
available

A DC powered electric centrifugal pump located in the RH collector tank provides a source of pressurized fuel supply for APU and engine start in flight, or on the ground if the engine feed ejector pump and AC power or the AC Fuel pump are not available. Electrical power will be supplied from the DC ESS BUS 2

86
Q

What turns on the DC pump for a battery eng start?

A

FADEC (Not sure what this question means)

87
Q

When starting the ENG what happens at 7%,20,50?

A

The FADEC initiates ignition at approximately 7% N2

the fuel flow (metering valve opens) at approximately 20% N2.

FADEC will automatically switch to the other ignitor if no light off is detected within 15 s after initiation of fuel flow. The start should be aborted if no light off is detected within 30 s after initiation of fuel flow.

After a light off occurs, the FADEC commands the starter to cutout at approximately 50% N2, and commands the FMU fuel metering valve to accelerate the engine to ground idle speed.

88
Q

What are the different ways to turn the AC fuel pumps on?

A

(not sure if this answers the question)
OFF: deactivates the associated AC fuel pump. automatically AUTO: operates the associated AC fuel pump according to the system’s logic.
ON: activates the associated AC fuel pump.

89
Q

AC Fuel Pumps are used for

A
  • Back-up for the ejector pumps
  • Used during crossfeed operations
  • AC Pump 2 provides fuel to APU when engine-driven pump (EDP) 2 is not running
90
Q

What mechanically can fail in an injector pump?

A

Nothing, only can get clogged

91
Q

When I have an engine failure what do I lose in regards to fuel?

A

All 4 kind of pumps

92
Q

What lbs is my fuel low?

A

660

the associated tank falls below 300 kg (660 lb), a low level warning will be provided to the crew.

93
Q

Can a fueler pump to a dark jet?

A

Yes through the DC hot bus

DC
Busses 1 and 2 provide power to the refuel control solenoids and the FCU. In BATTERY position, the system is powered by
HOT Bus 2. This allows fueling with the APU not running and no external power connected

94
Q

Max alt for apu operation

A

The APU operation is limited to 33,000 ft and AC electrical power can
be supplied up to this altitude

95
Q

Max start apu alt?

A

Its starting envelope is limited to 30,000 ft.

96
Q

Max eng start alt apu assisted?

A

APU bleed air is provided for the engine starting system up to 21,000 ft

97
Q

Max bleed apu alt?

A

– Bleed air for air conditioning and pressurization up to 15000 ft.

98
Q

Min temp for apu start?

A

Air Temperature
-54°C

The minimum battery temperature for an APU start -20°C

99
Q

APU starter limits?

A

Start Number 1&2
Maximum Time 60 seconds
Cool-Down Time 60 seconds

Start Number 3
Maximum Time 60 seconds
Cool-Down Time . 5 minutes

Before Stopping the APU After Engine Start:
Engine N2 must be stabilized …………………………….. for 5 seconds or power transfer confirmed on the Electrical Synoptic page.

Before Starting the APU After Engine is Shutdown:
Wait for engine to go below ……………………………………………30% N2

100
Q

APU starter limits?

A

Start Number 1&2
Maximum Time 60 seconds
Cool-Down Time 60 seconds

Start Number 3
Maximum Time 60 seconds
Cool-Down Time . 5 minutes

Before Stopping the APU After Engine Start:
Engine N2 must be stabilized …………………………….. for 5 seconds or power transfer confirmed on the Electrical Synoptic page.

Before Starting the APU After Engine is Shutdown:
Wait for engine to go below ……………………………………………30% N2

101
Q

How long is Apu cooldown?

A

Depends on APU either 2 minutes or 1 minute for APU FADEC 2.0 and on

102
Q

If I push the apu emer stop button what happens?

A

PUSH IN: closes the APU fuel shutoff valve, shutting down the APU with no cooldown period. A white striped bar
illuminates on the lower half of the button.

103
Q

What color is the sterile light in the back?

A

AMBER
An amber sterile light located on the cockpit/passenger partition indicates when entry into the cockpit is not allowed. An aural signal sounds whenever the sterile light is illuminated.

104
Q

Which ADS belong to what

A

1,2,3, cockpit
4, IESS
5, Flight control systems

105
Q

When I have an engine failure what do I lose in regards to fuel?

A

All 4 kind of pumps

CP (5 decks)

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