Power On Checks

Question 1

During exterior preflight verify brake accumulators are at what pressure?

Answer 1

700-800 psi

Question 2

Were are the brake pressure accumulators?

Answer 2

In the nose bay

Question 3

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

Answer 3

They should be OFF

Question 4

Were are the hydraulic system accumulators?

Answer 4

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

Question 5

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

Answer 5

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

Question 6

How many hydraulic systems are there?

Answer 6

3

Question 7

What is the normal system pressure

Answer 7

3000 psi

Question 8

Do the hydraulic systems share fluid

Answer 8

No

Question 9

How are the systems powered

Answer 9

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

Question 10

How are the back-up systems powered

Answer 10

Electrical, AC Motor Pump (ACMP)

Question 11

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

Answer 11

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

Question 12

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

Answer 12

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

Question 13

What does each hydraulic system power

Answer 13

Refer to hydraulic synoptic page

Question 14

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

Answer 14

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

Question 15

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

Answer 15

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

Question 16

During power on checks Nose steering should be ?

Answer 16

NOSE STEER-OFF

Question 17

What hydraulic system is active with the NOSE STEER-on

Answer 17

System #3

Question 18

Is NOSE STEER active in flight?

Answer 18

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

Question 19

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

Answer 19

55 degrees

Question 20

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

Answer 20

upto 7 degrees

Question 21

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

Answer 21

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

Question 22

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

Answer 22

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

Question 23

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

Answer 23

Up or 0 degrees

Question 24

Are the Flaps hydraulically or electically controlled

Answer 24

Electrically controlled

Question 25

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

Answer 25

Flaps will operate at half speed

Question 26

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

Answer 26

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

Question 27

What is the flaps 20 limit

Answer 27

231 Kts

Question 28

What is the flaps 30 limit

Answer 28

197 Kts

Question 29

What is the flaps 45 limit

Answer 29

189 Kts

Question 30

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

Answer 30

In the Stowed position

Question 31

What hydraulic systems powers the landing gear

Answer 31

#3

Question 32

What 3 thing happens when the Manual Release Handle is pulled

Answer 32

Releases the nose gear door uplock Releases Three landing gear uplocks dumps hydraulic pressure to allow gear to free fall

Question 33

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

Answer 33

by the #2 hydraulic system and downlock-assit actuators

Question 34

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

Answer 34

2100 psi

Question 35

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

Answer 35

No, needs presure from the # 3 hydraulic system

Question 36

During the Power On Checks what is the ADG Lever possition

Answer 36

Stowed

Question 37

What will cause the ADG to deploy

Answer 37

Complete loss of primary and aux power.

Question 38

Can the ADG be stowed once deploied

Answer 38

No

Question 39

What hydraulic system is run by the ADG

Answer 39

#3b

Question 40

What does the ADG Lamp test check

Answer 40

Serviceability of the Lamp only

Question 41

What does the test switch on the ADG do

Answer 41

performs a selftest

Question 42

Why do we perform the ADG test after the engine start

Answer 42

Two generators on-line are required

Question 43

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

Answer 43

The ADG is shrowded by an internal heating element

Question 44

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

Answer 44

Press the PWR TXFR OVERRIDE button

Question 45

What are the memory items associated with the ADG

Answer 45

ADG [PM] Pull, for 1 second then stow

Question 46

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

Answer 46

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

Question 47

What is the Main APU Battery primarily used for

Answer 47

Power to start the APU and supply backup DC power

Question 48

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

Answer 48

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

Question 49

The APU also provides power to what other Bus

Answer 49

DC emergency Bus

Question 50

What is the Volts and amps of the Main Battery

Answer 50

24 v 17 amp/hours

Question 51

What are the volts and amps of the APU Battery

Answer 51

24 Volts 43 amp/hours

Question 52

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

Answer 52

5 min due to insufficient cooling fo the displays

Question 53

What are the min volts for the Main and APU batteries

Answer 53

22 volts

Question 54

Which AC Bus recharges the Main Bat

Answer 54

AC Bus 1

Question 55

Which AC Bus charges the APU Battery

Answer 55

AC Bus 2

Question 56

How are the batteries monitored for over temp

Answer 56

By a sensor on each battery

Question 57

Conducting the Power on Checks ENG BOTTLES 1 &2 Test

Answer 57

Accomplish

Question 58

What areas have over heat detection

Answer 58

Zone B (Jet pipe and pylon) and MLG bay

Question 59

What areas have fire suppression

Answer 59

Zone A (Engine combustion section) and the APU

Question 60

How many fire bottles exist and were are they located

Answer 60

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

Question 61

Can both bottles be discharged into one engine

Answer 61

Yes, they are interconneted

Question 62

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

Answer 62

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

Question 63

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

Answer 63

Yes

Question 64

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

Answer 64

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

Question 65

On the Power on Checklist electiral power must be established. Who many ways can electircal power be established?

Answer 65

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

Question 66

Where is the AC EXT power receptacle

Answer 66

Foward right side of the fuselage

Question 67

Where is the DC EXT power receptacle located

Answer 67

Rear right side of fuselage below the right engine

Question 68

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

Answer 68

AC power is connected with proper voltage, frequency and phase

Question 69

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

Answer 69

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

Question 70

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

Answer 70

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

Question 71

When will the starter cutout while starting the APU

Answer 71

Between 35-45%

Question 72

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

Answer 72

90 Sec; to let the electrical system to power up

Question 73

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

Answer 73

Yes, by following the MEL 28-25-1

Question 74

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

Answer 74

10 min due to insuffient cooling of generator adapter oil

Question 75

What are the start limitations of the APU using battery power

Answer 75

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

Question 76

What are the APU Starting limits using ground power

Answer 76

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

Question 77

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

Answer 77

APU use is prohibited

Question 78

What is the maximum operating altitude of the APU

Answer 78

20,000 feet

Question 79

What is the maximun altitude that the APU can be started

Answer 79

20,000 feet

Question 80

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

Answer 80

30 kVA

Question 81

What is the maximum altitude for bleed air use

Answer 81

15,000

Question 82

Minimum ambient temp for APU start

Answer 82

-40

Question 83

What is the in-flight APU start envelope limit

Answer 83

141-290