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Normal Checklist for Flight > Power On Checks > Flashcards

Power On Checks Flashcards

1
Q

During exterior preflight verify brake accumulators are at what pressure?

A

700-800 psi

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2
Q

Were are the brake pressure accumulators?

A

In the nose bay

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3
Q

During Power On Checks: On overhead panel starting with hydraulics, what possition should the hydaulic switche be in?

A

They should be OFF

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4
Q

Were are the hydraulic system accumulators?

A

System 1 and 2 are in the aft equipment bay. System 3 can be seen from the access panel below the luggage door.

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5
Q

What should the hydraulic systems read prior to power on and why?

A

1450-1550 psi. Each accumultare is precharged with nitrogen to 1500 psi

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6
Q

How many hydraulic systems are there?

A

3

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7
Q

What is the normal system pressure

A

3000 psi

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8
Q

Do the hydraulic systems share fluid

A

No

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9
Q

How are the systems powered

A

System 1A and 2A are engine driven. 3A, 1B, 2B and 3B are AC motor driven

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10
Q

How are the back-up systems powered

A

Electrical, AC Motor Pump (ACMP)

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11
Q

When do the back-up pumps activate with the switch in the auto

A

1B and 2B whenever the opposite generator is on-line and the flaps are greater than 0 degrees (more than 4 degrees). 3B also activates when the Flaps are greater than 0 degrees or when the ADG is deployed

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12
Q

Do you have to move 3B to the on position if there is an dual gen failure

A

No, only 1B and 2B are related to generators

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13
Q

What does each hydraulic system power

A

Refer to hydraulic synoptic page

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14
Q

What indication would you get if htere was inadequate pressure to operated the FLT SPLR

A

Amber FLT SPLR on hydraulic synoptic page, system 1 or 2

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15
Q

If gererator #2 fails what hppens to 1B hydraulic pump? Why?

A

It is load shed because this is the cross side generator that has to be on for the pump to activate when the flaps are greater than 0 degrees

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16
Q

During power on checks Nose steering should be ?

A

NOSE STEER-OFF

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17
Q

What hydraulic system is active with the NOSE STEER-on

A

System #3

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18
Q

Is NOSE STEER active in flight?

A

No, it is deactivated in flight because the PSEU “gound” mode is not satisfied.

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19
Q

With the NOSE STEER-on how many dergrees can the nose turn?

A

55 degrees

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20
Q

With the NOSE STEER-on how many degrees will the nose turn with the rudder peddles only?

A

upto 7 degrees

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21
Q

If using differential braking and nose steer is on what could happen

A

Possbly exceed the 55 degree limit and system will automaticly disable and nose wheel will automaticly free caster to a maximum of 99 degrees

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22
Q

If NOSE STEER has exceeded the 55 degree limit how is the system reactivated

A

Nose wheel must be placed or moved back into the 55 degree limit.

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23
Q

During Power on Checks the flap handle should be in what possition?

A

Up or 0 degrees

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24
Q

Are the Flaps hydraulically or electically controlled

A

Electrically controlled

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25
Q

If a motor in the Flaps Power Drive Unit (PDW) fails what happens to the flaps

A

Flaps will operate at half speed

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26
Q

The FLAPS FAIL amber message can indicate two issues, what are they?

A

Complete failure in the flap system or an asymmetry >2.75 degrees exist .

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27
Q

What is the flaps 20 limit

A

231 Kts

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28
Q

What is the flaps 30 limit

A

197 Kts

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29
Q

What is the flaps 45 limit

A

189 Kts

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30
Q

During Power on checks were should the Manual Release Landing Gear handle be

A

In the Stowed position

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31
Q

What hydraulic systems powers the landing gear

A

3

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32
Q

What 3 thing happens when the Manual Release Handle is pulled

A

Releases the nose gear door uplock

Releases Three landing gear uplocks

dumps hydraulic pressure to allow gear to free fall

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33
Q

Since the nose gear is assisted into the down-and-locked position with airflow downlock-assit springs, how is the MLG assited into the down-and-locked position

A

by the #2 hydraulic system and downlock-assit actuators

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34
Q

At what PSI level will the # 3 hydaulic system fail to allow gear extention

A

2100 psi

35
Q

If the alternat gear extention us used will the nose door close

A

No, needs presure from the # 3 hydraulic system

36
Q

During the Power On Checks what is the ADG Lever possition

A

Stowed

37
Q

What will cause the ADG to deploy

A

Complete loss of primary and aux power.

38
Q

Can the ADG be stowed once deploied

A

No

39
Q

What hydraulic system is run by the ADG

A

3b

40
Q

What does the ADG Lamp test check

A

Serviceability of the Lamp only

41
Q

What does the test switch on the ADG do

A

performs a selftest

42
Q

Why do we perform the ADG test after the engine start

A

Two generators on-line are required

43
Q

What prevents the ADG from freezing up after being cold soak at altitude

A

The ADG is shrowded by an internal heating element

44
Q

If a generator comes back on-line how do you disengage the ADG

A

Press the PWR TXFR OVERRIDE button

45
Q

What are the memory items associated with the ADG

A

ADG [PM] Pull, for 1 second then stow

46
Q

How many batteries are there on the 650 and were are they located

A

Two, Main battery in the nose; APU battery is in the Aft equiment bay

47
Q

What is the Main APU Battery primarily used for

A

Power to start the APU and supply backup DC power

48
Q

The Main Battery is also a source of emergeny power to what 2 things

A

EICAS Data Concentrator Units (DCU’s) and Emer Bus

49
Q

The APU also provides power to what other Bus

A

DC emergency Bus

50
Q

What is the Volts and amps of the Main Battery

A

24 v 17 amp/hours

51
Q

What are the volts and amps of the APU Battery

A

24 Volts 43 amp/hours

52
Q

How long can the Main Battery be used as the only source of power to the aircraft and why

A

5 min due to insufficient cooling fo the displays

53
Q

What are the min volts for the Main and APU batteries

A

22 volts

54
Q

Which AC Bus recharges the Main Bat

A

AC Bus 1

55
Q

Which AC Bus charges the APU Battery

A

AC Bus 2

56
Q

How are the batteries monitored for over temp

A

By a sensor on each battery

57
Q

Conducting the Power on Checks ENG BOTTLES 1 &2 Test

A

Accomplish

58
Q

What areas have over heat detection

A

Zone B (Jet pipe and pylon) and MLG bay

59
Q

What areas have fire suppression

A

Zone A (Engine combustion section) and the APU

60
Q

How many fire bottles exist and were are they located

A

3, in the aft equipment bay. The engin fire bottles are under the APU and the APU fire bottle is adjacent to the APU compartment

61
Q

Can both bottles be discharged into one engine

A

Yes, they are interconneted

62
Q

What six things happen when the ENG FIRE PUSH Switch/light is pushed

A
  1. squibs are armed
  2. Engine generator shuts down
  3. Fuel hutoff valve closes
  4. Hudaulic shutoff valve closes
  5. Bleed air shutoff valve closes
  6. Engine igniter disabled
63
Q

If a fire or overheat conditions is detected by the APU Fire/Overheat Protection will the APU shut down automaticlly

A

Yes

64
Q

What are the six things that occur when the APU FIRE PUSH Switch/Light is pushed

A
  1. squib is armed
  2. APU shuts down
  3. APU fuel shutoff valve closes
  4. APU neg-g shutoff valve closes
  5. APU LCV clsoes
  6. APU gen shuts down
65
Q

On the Power on Checklist electiral power must be established.

Who many ways can electircal power be established?

A
  1. Start the APU
  2. connect external power
  3. Start right engine
66
Q

Where is the AC EXT power receptacle

A

Foward right side of the fuselage

67
Q

Where is the DC EXT power receptacle located

A

Rear right side of fuselage below the right engine

68
Q

What does the AVAIL light on the EXT POWER AC withc/light mean when it is illuminated

A

AC power is connected with proper voltage, frequency and phase

69
Q

What does the IN USE light on the ELECTRICAL POWER overhead panel mean if it is illuminated

A

DC power is cnnected to the aircraft and suppling power directly to the APU BATT DIR BUS

70
Q

What are the 5 things that happen when you push the APU PWR FUEL switch light

A
  1. Activates the APU control unit
  2. APU fuel pump (right main tank)
  3. opens the SOV
  4. Opens the Neg-G SOV
  5. Activates the EICAS message
71
Q

When will the starter cutout while starting the APU

A

Between 35-45%

72
Q

After the APU is started and electircal power is established to the aircraft, how long do you wait before continueing the checklist and why

A

90 Sec; to let the electrical system to power up

73
Q

If there is an APU Pump cautions message can you still start the APU

A

Yes, by following the MEL 28-25-1

74
Q

If the APU is started by alternat means what is the time limit and why

A

10 min due to insuffient cooling of generator adapter oil

75
Q

What are the start limitations of the APU using battery power

A

Three 30-second start attempts of continous cranking, followed by 20 min of cooling

Two furthre 30-second attempts of continous cranking

If start is not successful do not attempt additional starts for 35 min

76
Q

What are the APU Starting limits using ground power

A

Two 15-sec start attempts of continuous cranking followed by 20-min cooling

Two further 15-sec attempst of continuous cranking

If start not successful do not attempt to start for at least 35-min

77
Q

During single engine flight operations can I use the APU bleed air to start the failed engine

A

APU use is prohibited

78
Q

What is the maximum operating altitude of the APU

A

20,000 feet

79
Q

What is the maximun altitude that the APU can be started

A

20,000 feet

80
Q

At 20,000 feet how many kVA will the APU generator produce

A

30 kVA

81
Q

What is the maximum altitude for bleed air use

A

15,000

82
Q

Minimum ambient temp for APU start

A

-40

83
Q

What is the in-flight APU start envelope limit

A

141-290

84
Q
A

Normal Checklist for Flight (3 decks)

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