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Initial SAI 737-800 (NO 400) > Just Another Deck > Flashcards

Just Another Deck Flashcards

1
Q

PSEU LIGHT:

What does it mean?

A

Proximity Switch Electronic Unit

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2
Q

PSEU LIGHT:

What does it

A

Takeoff Configuration Warnings
Landing Configuration Warnings
Landing Gear
Air/Ground Sensing

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3
Q


What will happen if the stabilizer trim is operated with the autopilot engaged?

A

It will disengage

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4
Q

How many degrees will the tiller deflect the nose gear?

A

78 degrees (75 degree effective turn) – 1.10.2

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5
Q

What is the minimum pavement width for a 180 degree turn?

A

73 feet – 1.10.2 FOM 93 feet

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6
Q

What describes the largest arc during a turn?


A

The tail (68 feet from rotation point; just inside of inside gear) – 1.10.2

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7
Q

What is the first light that should illuminate when we move the IRS Mode Selector to the NAV position?

What should we see after that?

-How long does it take to complete a normal alignment?

A
  • The ON DC light should illuminate, indicating a short power test is being performed. – 11.20.4
  • ON DC light will extinguish, the ALIGN light will illuminate, and the alignment process will illuminate. – 11.20.4
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8
Q

Is there any way to monitor how long until the alignment process is complete? 11.10.10

A

Yes. By selecting “HDG/STS” on the IRS DISPLAY’s Display Selector. (it will display seven minutes until 6 minutes remain during the alignment process, and then will display the actual amount of time remaining).

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9
Q

What does it mean if the ALIGN light is flashing? 11.10.11

A

. 1) A significant difference between the previous and entered position (unreasonable present position) 


. 2) No present position entered 


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10
Q

During the Secure Procedure, when the IRS Mode Selector is moved to OFF, what should you see on the IRS Mode Selector Unit?

A

The ALIGN light should illuminate until the system is completely shut down (approximately 30 seconds). 11.20.6

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11
Q

If AC power is lost, where do the IRSs get their electrical power? 11.20.6

A

The switched hot battery bus.

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12
Q

How long will each IRS operate if AC power is lost? 11.20.6; 11.11

A

The left for as long as DC power is available; DC power to the right IRS is automatically terminated if AC power is not restored within 5 minutes.

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13
Q

Is there a system to warn people on the ground that the IRSs are operating and AC power has been lost? 11.20.6

A

Yes. Warning horn in the wheel well will sound.


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14
Q

Name one reason that the REVERSER light on the aft overheard panel would be illuminated. 7.10.14

A

The REVERSER light on the aft overhead panel will illuminate for one or more of the following reasons:

		- Isolation valve or thrust reverser control valve is not in the commanded position 

		- Thrust reverser sleeve position sensors are in disagreement 

		- Auto-reset circuit has been activated 


The REVERSER light illuminates when the thrust reverser is commanded to stow and extinguishes 10 seconds later when the isolation valve closes. Any time the REVERSER light illuminates for more than approximately 12 seconds, a malfunction has occurred, and the MASTER CAUTION and ENG system annunciator lights illuminate.

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15
Q

Since the oxygen bottles next to the supernumerary seats are not controlled by the passenger oxygen switch, does that switch even do anything on our airplanes?

A

Yes.

It activates the passenger oxygen in the lavatory

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16
Q

What are the PMC’s? 7.20.2 


A

Power Management Control.

The PMCs, along with the Main Engine Control, make up the thrust management system. 


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17
Q

With the PMCs operational, do we have complete protection from overboost if the thrust levers are advanced to the full forward position? 7.20.1


If one of them fails, can we still depart?

If yes, are we allowed to utilize the operable PMC? L.10.6

A


No. Some overboost will still occur if the thrust levers are advanced to full forward even with the PMCs operational.

L.10.6 Yes

NO, Refer to the DDG

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18
Q

What do the PMCs do?

A

7.20.2
The PMC uses MEC power level angle, N1 speed, and inlet temperature and pressure to adjust, or trim, the MEC to obtain the desired N1 speed. The PMC adjust fuel flow as a function of thrust level angle.
Provides a constant thrust climb feature. Once climb thrust is set, the PMC maintains the desired thrust throughout the climb profile without the need for further thrust lever movement.

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19
Q

If the PMC fails or is selected off, how is engine speed controlled? 7.20.2

A

By the hydro-mechanical MEC only.

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20
Q

Will the PMC INOP light be illuminated prior to engine start? 7.20.2

A

No. It is suppressed below starter cutout engine speed.

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21
Q

How many engine idle speeds are there? 7.20.2

A

Two

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22
Q

What are they? 7.20.2

A

High and Low

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23
Q

Is it normal to see the LOW IDLE light illuminated in flight? 7.20.2

A

No.

The minimum speed for all flight phases is high idle

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24
Q

Is high idle the same engine speed for all flight conditions? 7.20.2

A

No.

As temperature and airspeed decrese, high idle speed also decreases. The average high idle setting is 32% N1.

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25
Q

What percent N1 is low idle speed, and when is it automatically selected? 7.20.2

A

Approximately 22%; four seconds after touchdown.

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26
Q

What purpose does low idle serve? 7.20.2


A

It reduces braking activity and stopping distance.

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27
Q

What is the purpose of the four second delay? 7.20.2

A


It provides enhanced engine speed acceleration for reverse thrust.

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28
Q

When will the LOW IDLE light on the aft overhead panel illuminate? 7.10.14

A
  • Thrust lever for either engine is near idle and the MEC on either engine is not commanded to maintain high idle in flight 

    • The speed of either engine is below 25% N1 in flight
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29
Q

What happens when the MAIN CARGO COMPARTMENT AIR SUPPLY SHUTOFF switch is moved to the off position? 2.10.7

A

Airflow to the main cabin is shutoff, while airflow to the flight deck continues.

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30
Q

When does the Flight Recorder operate? 14.20.8

A
  • In flight – When Transfer Bus 1 is powered 

    • On Ground – Transfer Bus 1 is powered AND either engine is operating 
When is the cockpit voice recorder active? 5.1.10
Anytime 115 volt AC power is applied to the airplane. 

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31
Q

How can you silence the Mach/Airspeed Warning System if you are exceeding Vmo/Mmo? 15.20.8

A

You can only silence it by slowing below Vmo/Mmo 


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32
Q

If the captain’s stick shaker fails inflight, and the aircraft subsequently approaches a stall, will the captain’s yoke still vibrate? 15.10.3

A


Yes. Vibrations are felt in both columns though control interconnects when either stick shaker activates. 


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33
Q

Can a single hydraulic system operate all primary flight controls? 9.20.1

A

Yes

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34
Q

What primary flight controls may still be operated with the loss of all hydraulic systems? 9.20.1

A

Ailerons and elevators (control forces will be higher due to friction and aerodynamic loads)

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35
Q

Can the rudder still be operated with the loss of both A and B hydraulic systems? 9.20.1

A

Yes.

Through the standby hydraulic system.

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36
Q

What happens when the FLT CONTROL switch is moved to the OFF position? 9.10.1 


A

Closes the flight control shutoff valve isolating the ailerons, elevators, and rudder from associated hydraulic system pressure.

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37
Q


What two ways can we manual activate the Standby Hydraulic Pump? 13.20.4 


A
  • Positioning either FLT CONTROL switch to STBY RUD 


- Positioning the ALTERNATE FLAPS master switch to ARM

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38
Q

What happens when the FLT CONTROL switch is moved to STBY RUD? 13.20.4

A
  • Activates the standby electric motor-driven pump 

  • Shuts off the related hydraulic system pressure to ailerons, elevators and rudder by closing 
the flight control shutoff valve 

  • Opens the standby rudder shutoff valve 

  • Deactivates the related flight control LOW PRESSURE light when the standby rudder shutoff 
valve opens 

  • Allows the standby system to power the rudder and thrust reversers 

  • Illuminates the STBY RUD ON, Master Caution, and Flight Controls (FLT CONT) lights. 

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39
Q

What happens when the ALTERNATE FLAPS master switch is moved to ARM? 13.20.4 


A
  • Activates the standby electric motor-driven pump 

  • Closes the trailing edge flap bypass valves 

  • Arms the ALTERNATE FLAPS position switch 

  • Allows the standby system to power the leading edge slaps and slats and thrust reversers 

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40
Q

What will cause Automatic Operation of the standby hydraulic system? 13.20.5

A
  • Loss of system A or B, or rudder pressure reducer system fails in low pressure mode, and 

  • Flaps extended, and 

    • Airborne or wheel speed greater than 60 knots, and 

    • FLT CONTROL switch A or B hydraulic system ON 
OR 

    • The main PCU Force Fight Monitor (FFM) trips

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41
Q

What does automatic operation of the Standby Hydraulic system cause?13.20.5

A
  • Opens the standby rudder shutoff valve
- Activates the standby electric motor-driven pump
- Allows the standby system to power the rudder and thrust reversers
- Illuminates the STBY RUD ON, Master Caution, and Flight Controls (FLT CONT) lights 

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42
Q

What is the Elevator Feel System? 9.20.6

A


The elevator feel system uses the elevator feel computer to provide simulated aerodynamic forces using airspeed (from the elevator pitot system) and stabilizer position. Feel is transmitted to the control columns by the elevator feel and centering unit. To operate the feel system the elevator feel computer uses either hydraulic system A or B pressure, whichever is higher. 
When either hydraulic system or elevator feel pitot system fail, excessive differential pressure is sensed in the elevator feel computer, and the FEEL DIFF PRESS light illuminates

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43
Q

When is the Feel Differential Pressure light armed? 9.10.3

A

Trailing edge flaps are up

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44
Q


What does it mean if the light is illuminated? 9.10.3

A

Excessive differential pressure in the elevator feel computer

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45
Q


What is the Speed Trim System? 9.20.9

A

The speed trim system is designed to improve flight characteristics during operations with a low gross weight, aft CG, high thrust. It monitors inputs of stabilizer position, thrust lever position, 
airspeed, and vertical speed and then trims the stabilizer using the autopilot stabilizer system. Operates most frequently during takeoff and go-arounds

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46
Q

Conditions for speed trim operations:

A
  • Flaps up or down 

  • Airspeed 100 – 300 KIAS 

  • 10 seconds after takeoff 

  • 5 seconds following release of trim switches 

  • N1 above 60% 

  • Autopilot not engaged 

  • Sensing of a trim requirement 

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47
Q

What is indicated if the SPEED TRIM FAIL light illuminates when the Master Caution recall light recall is pressed, and extinguishes when the master caution system is reset? 9.10.3

A


Failure of a single FCC channel

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48
Q

Will the system still operate?

A

Yes


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49
Q

What is Mach Trim? 9.20.6 


A

Above Mach .615, the Mach trim system automatically adjusts the elevators with respect to the stabilizer as speed increases.

The Mach trim actuator repositions the elevator feel and centering unit, which adjusts the control column neutral position. 


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50
Q

In flight, you notice that both your EADI and EHSI go completely blank at the same time. What is the likely cause of this, and is there anything that you can do to restore your displays? 10.40.1, 10.32.29 


A

The onside symbol generator has failed. The display can be restored by selecting the Electronic Flight Instrument (EFI) switch to Both on the operating side. 


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51
Q

What is indicated by the FUEL VALVE CLOSED light being illuminated bright blue? 12.10.1

A

The related fuel shutoff valve: 


		- Is in transit, or 

		- Valve position and engine start level or engine fire switch disagree 

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52
Q

Which valve position is indicated by the FUEL VALVE CLOSED light?

A

12.10.1 The Engine fuel shutoff valve.

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53
Q

Are the fuel valves and crossfeed valve AC or DC powered?

A

DC 


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54
Q

From what bus? 12.20.2

A

Hot battery bus

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55
Q

From which tank is the fuel temperature sensed? 12.10.1

A

Number one tank.

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56
Q

If the fuel filter bypass light illuminates, what is indicated? 12.10.2

A

Impending fuel filter bypass due to a contaminated filter.

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57
Q

Can you feed fuel to the APU from the number two tank?

If so, how? 7.30.1

A


Yes. Open the crossfeed selector and turn on either of the number two AC fuel pumps.

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58
Q

If AC fuel pumps are not operating, how is fuel supplied to the APU? 7.30.1, 7.30.2

A

Fuel is suction fed to the APU from the number 1 tank if the AC fuel pumps are not operating. On some airplanes, a DC fuel pump provides positive fuel pressure to the APU, but only until the APU is at governed speed and ready to accept a load.

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59
Q

With all six fuel pumps in the off position, how many fuel pump LOW PRESSURE lights should be illuminated? 12.10.2, 12.10.3

A

4, The center tank low pressure lights will not be illuminated when the pump switches are in the off position

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60
Q

In flight, both center fuel tank pump low pressure lights and the Master Caution light illuminate, causing you to turn off the center tank pumps even though there is fuel remaining in the center tank. What happens to the fuel that remains in the center tank? 12.20.4

A

When the center tank pump switches are both turned off, the fuel scavenge shutoff valve opens, allowing fuel from the number 1 forward main tank to operate the center tank scavenge jet pump.

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61
Q

How long will the scavenge pump operate? 12.20.4


A

20 minutes after the center wing tank pumps are turned off.

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62
Q

Where is the fuel scavenged to? 12.20.

A

Main tank 1

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63
Q

Which tanks can be pressure refueled? 12.20.3

A

Both main tanks and the center tank

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64
Q

If pressure fueling is not available, which tanks can be filled directly using over wing fueling?

A

12.20.3 Both main tanks.

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65
Q

Is there any way to get fuel into the center tank if pressure refueling is not available? 12.20.3

A

Yes. Through ground tank to tank fuel transfer

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66
Q

What are the approximate fuel tank quantities? 12.20.4

A

Each main tank – 8,630
Center tank – 28,803
Total tank capacity – 46,063

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67
Q


I walk onto a completely dark airplane and want to apply power to it. How do I do that? SP.6.1

A

The Electrical Power Up Supplementary Procedure


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68
Q

What are the phase, volts, and cycles of the AC electrical system? 6.20.1

A

3 phase, 115 volts, 400 hz


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69
Q

What are the different sources of normal AC electrical power?6.20.1

A

Main engine generators, APU generator, AC external

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70
Q

Can the different sources of AC power be paralleled? 6.20.1

A

No


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71
Q

How do the engine generators provide electrical power at a constant frequency? 6.20.1

A

Through a generator drive unit that maintains a constant frequency throughout the normal operating range of the engine

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72
Q

What is indicated by a “RISE” indication of the Generator Drive Oil Temp of more than 20 degrees C? 6.20.6

A

Excessive generator load, or poor generator drive condition.

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73
Q

If the Generator Disconnect switch is used to disconnect the generator, can the generator be re-engaged in flight? 6.10.4

A

No


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74
Q

Does the APU have a generator drive unit? 6.20.1

A

No
Why not? 6.20.1

It is not needed since the APU is governed to maintain a constant speed.

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75
Q

Can the APU power both Generator Busses while on the ground? 6.20.4

A

Yes.


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76
Q

Can the APU power both Generator Busses in flight? 7.30.1

A

No.


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77
Q

What is the purpose of the Bus Transfer system? 6.20.4

A

Allows the AC transfer busses to be powered from the offside GEN Bus in the event that the onside generator bus becomes unpowered (occurs automatically with the switch in the AUTO position).

78
Q

With the loss of all AC generators, how is the Standby Bus powered? 6.20.10

A

From the battery, through a static inverter.

79
Q

In flight, with the STANDBY POWER switch in AUTO, and the loss of all AC generators, what will happen? 6.20.10

A

The AC standby bus will be powered from the battery via a static inverter, and the DC standby bus, battery bus, and switched hot battery bus are powered by the battery.

80
Q

With the STANDBY POWER switch in the AUTO position, and the loss of all AC generators, what will happen upon touchdown? 6.20.10

A

Air ground logic will prevent the battery from continuing to power the AC and DC standby busses. As a result, all equipment powered by the AC and DC standby busses is lost until the STANDBY POWER switch is moved to the BAT position.

81
Q

How long will a fully charged battery continue to provide power to the essential flight instruments following the loss of all AC generators? 6.20.10

A

At least 30 minutes


82
Q

How do we produce DC power on the airplane? 6.20.8

A

Three transformer Rectifier Units convert 115 volt AC power to 28 volt DC power

83
Q

How many batteries do we have on our airplanes?

A

One


84
Q

How many volts is the battery? 6.20.8

A

24 volts


85
Q

Are DC Bus 1 and 2 generally paralleled? 6.20.8

A

Yes. Via the TR 3 disconnect relay.


86
Q

What happens in the DC electrical system during a flight director or autopilot approach? 6.20.8

A

The TR 3 disconnect relay automatically opens to prevent a single failure from affecting both navigation receivers and flight control computers.

87
Q

With the battery switch off, and ground power available, can I connect external AC ground power? 6.20.2

A

No

88
Q

Can we start the APU with the airplane battery switch in the OFF position? 7.30.2

A

No

89
Q

If the APU is running and the battery switch is moved to the OFF position, will the APU shutdown? 7.30.2

A

On the ground – Yes

In flight – No


90
Q

If the APU Maintenance light is illuminated, can we operate the APU? 7.10.6

A

Yes


91
Q

The Low Oil Pressure light illuminates during an APU start attempt. Is this normal? 7.10.16

A

Yes

92
Q

What will cause the APU to automatically shutdown? 7.10.16-17, 8.20.4

A
  • APU Low oil pressure (after start cycle is complete) - APU overspeed
- APU Fault
- APU Fire
93
Q

What is the function of the Equipment Cooling System? 2.31.6


A

It cools electronic equipment on the flight deck and in the E&E bay.

94
Q

Is there any indication to ground personnel that there is a problem with the system? 2.31.6

A

The crew call horn in the nose wheel well will sound.

95
Q

In flight, what is the E&E cooling air used for? 2.31.6


A

It is used to warm the lower forward cargo compartment

96
Q

With the Emergency Exit Lights switch in the ARMED position, what will cause the emergency lights to illuminate automatically? 1.30.6

A
  • Electrical power to DC Bus 1 fails 


- AC power is removed from the aircraft

97
Q

Why would we want to use the ON position as opposed to the AUTO position for the Supernumerary signs? 1.40.4

A


In auto: 


  • the no smoking sign will extinguish when the gear is retracted. 

  • Seat belt/return to seat signs will extinguish when the flaps and gear are retracted 

98
Q

With the window heat selected on, and the green ON light extinguished, is there a problem with the window heat? 3.10.1 


A

Can’t tell by this indication alone. There could be an overheat or failure, or the window may simply be at the correct temperature.

99
Q

Which of the windows is not electrically heated? 3.20.2

A

Window L3/R3

100
Q

Which surfaces are protected by the Wing Anti-Ice? 3.20.4

A

The slats (but not the leading edge flaps)

101
Q

Will the wing anti-ice work on the ground? 3.20.5

A

Yes.

102
Q

Will the wing anti-ice work with the slats extended? 3.20.4

A

Yes

103
Q

With the wing anti-ice selected on while on the ground, what will cause the wing anti-ice valves to close? 3.20.5

A
  • Either engine thrust is above the takeoff warning setting, or 

  • Either temperature sensor detects a duct over temp
104
Q

Will the wing anti-ice valves reopen when the thrust levers are retarded below the takeoff warning position? 3.20.5

A

Yes


105
Q

When will the wing anti-ice switch automatically trip to the off position? 3.20.5

A

At lift-off


106
Q

Will the engine anti-ice work both in flight and on the ground? 3.20.3

A

Yes

107
Q

Will engine anti-ice function with the engine bleed air switch in the OFF position? 3.20.4

A

Yes


108
Q

What stage bleed air does the anti-ice use? 3.20.4

A


5th and 9th; the same as the pneumatic system

109
Q

What is indicated if the amber COWL ANTI-ICE light illuminates? 3.20.3

A

Over temp or over pressure 


110
Q

If the COWL VALVE OPEN light remains illuminated bright blue with the engines at idle, what can be done to correct the issue? SP.16.10

A

Increase engine thrust slightly (minimum of 30%) 


111
Q

How many hydraulic systems do we have, and what are they? 13.10.1 3;

A

A, B, Standby

112
Q

What is the normal pressure of the hydraulic systems? 13.10.2

A

3,000 psi

113
Q

What are the maximum and minimum hydraulic system pressures? NP.21.32, 34, 13.10.2

A

3,500; 2,800

114
Q

What is the minimum hydraulic system quantity?

A

88% (only valid on the ground)

115
Q

What systems are powered by the hydraulic systems? 13.20.1

A
  • flight controls 

  • leading edge flaps and slats 

  • trailing edge flaps 

  • landing gear 

  • wheel brakes 

  • nose wheel steering 

  • thrust reversers 

  • autopilots
116
Q

Is there any decrease in airplane controllability with the loss of a single hydraulic system? 13.20.1

A

No

117
Q

With regard to the hydraulic system, what is the bleed air system used for?13.20.1

A

It is used to pressurize the reservoirs

118
Q

What kind of pumps do hydraulic systems A and B have? 13.20.1


A

1 engine driven pump, and one AC electric motor-driven pump per system

119
Q

Which pump provides more fluid volume? How much? 13.20.2

A

The engine driven pumps; approximately four times

120
Q

How is the hydraulic fluid cooled? 13.20.2 


A

A heat exchanger located in the fuel tanks (A system in main tank 1, and B system in main tank 2).

121
Q

What is the minimum fuel required in the main fuel tank in order for the associated electric pump to be selected on on the ground? 13.20.3

A

1,675 pounds


122
Q

If a leak develops in one of the engine driven hydraulic pumps, will all fluid quantity be lost? 13.20.3

A

No. A standpipe in the reservoir will prevent total system loss if a leak develops in the engine driven hydraulic pump or related lines (22% for system A, 40% for system B).

123
Q

Will all system quantity be lost if a leak develops in the electric motor driven pump? 13.20.3

A

Yes.

124
Q

System B hydraulic quantity is lost a result a leak in the electric motor driven pump. Will the power transfer unit still function? 13.20.3

A

Yes, Sufficient fluid quantity will remain for operation of the power transfer unit.

125
Q

If a leak develops in the standby hydraulic system, will system B also be lost? 13.20.7

A

No. Although the hydraulic system B quantity will decrease until indicating approximately 64%.

126
Q

If the engine driven pump switch is selected off, does the pump stop moving? 13.20.2

A

No. The pump continues to rotate, but the pump is isolated from the rest of the system.

127
Q

What systems can be powered by the standby hydraulic system? 13.20.4

A
  • Thrust reversers 

  • Rudder 

  • Leading edge flaps and slats (extend only)
128
Q

Is there a light that tells us that the main deck cargo door not being sensed in the closed position? 1.30.9

A

Yes. Located on the center instrument panel.

129
Q

Could the door accidentally be operated in flight using the hydroelectric pump? 1.40.21

A

No. The door is electrically un-powered in flight.

130
Q

What is the wind limit for the entry, service, and lower cargo doors? 1.30.11

A

Do not operate the entry or lower cargo doors with winds at the door of more than 40 knots.

Do not keep entry or lower cargo doors open when wind gusts are more than 65 knots. –

131
Q

With external ground power connected, and the battery switch in the OFF position, can the main deck cargo door be positioned using the electrical pump? 1.40.21

A

No. DC Bus 2 must be powered in order to operate the electric hydraulic pump.


132
Q

Is there another means to open the door that will work without the application of electrical power?

A

Yes. A hand operated hydraulic pump is available.

133
Q

How do we provide warmer air for the zones which need warmer air? 2.31.4

A

Using the trim air system.

134
Q

When does a dual bleed situation exist? L.10.6

A
  • APU bleed air valve open and number 1 engine bleed air valve open 

  • APU bleed air valve open, isolation valve open, and number 2 engine bleed air valve open 

  • APU bleed air valve open, isolation valve open, and ground air connected 

135
Q

Which of the dual bleed configurations will not result in the dual bleed light being illuminated? 2.20.1

A

Ground air connected with the APU bleed air valve open and isolation valve open

136
Q

When will the RAM AIR doors move to the full open position? 2.31.2

A

On the ground, or in flight with the flaps out of up.

137
Q

With both AC packs operating, and the switch in AUTO, will the packs regulate to high or low flow? 2.10.4

A

Low flow


138
Q

With only one pack operating, and the switch in auto, what will happen? 2.10.4

A

The pack will regulate to high flow.


139
Q

What happens when the ENGINE START switch is moved to the GRD position? 7.10.12 


A
  • Opens the start valve 

  • Closes the engine bleed air valve 

  • Provides ignition to the selected ignitor(s) when the engine start lever is moved to IDLE 

140
Q

What is the difference between the CONT and FLT positions on the ENGINE START switches? 7.20.12

A

On Ground, ignition is provided to the selected ignitor(s) when engine start lever is in IDLE. In FLT, ignition is provided to both ignitors (regardless of ignitor selection) when the engine start lever is in IDLE 


141
Q

Which ignition system, Left or Right, is considered more critical? Why?

A


The right is more critical, since it is powered by the AC Standby Bus, and would therefore still be powered even with the loss of all AC gens (Left is powered by the AC Transfer Bus).

142
Q

So, the inboard and outboard landing lights are those lights in the wing root. Right? 1.40.1

A

No. Those are the inboard landing lights and the runway turnoff lights.

143
Q


Where are the outboard landing lights? 1.40.1

A

The outboard flap fairing

144
Q

What hydraulic system powers landing gear extension and retraction? 14.20.1

A

System A 


145
Q

Is there an alternate means for extending the landing gear if system A hydraulics are lost? 14.20.2

A

Yes. The manual gear extension system releases the uplocks and allows the gear to extending via gravity and air loads.

146
Q

What is the Landing Gear Transfer Unit? 13.20.4

A

It supplies pressurized hydraulic fluid needed to raise the landing gear at the normal rate when system A is lost due to number 1 engine RPM loss. The B system engine driven pump supplies the pressurized hydraulic fluid needed to operate the landing gear transfer unit.

147
Q

When does the Landing Gear Transfer Unit operate? 13.20.4

A

When all of the following conditions exist:

  • airborne
- number 1 engine RPM drops below a limit value
  • LANDING GEAR lever is positioned up

  • Either main landing gear is not up and locked
148
Q

With the landing gear up and the flaps set to 15 degrees, can you silence the landing gear warning horn?

BAD Q

A

No. Because flaps 15 is a landing flap setting.
More to it than this. Bad question.
If the primary landing gear indication system isn’t functioning, how would we verify that the main landing gear is down and locked?
Via the secondary main landing gear down and lock indicators on the after overhead panel.

149
Q

What hydraulic system is primary for nosewheel steering? 14.20.3

A

System A


150
Q

How does the alternate nosewheel steering system powered? 14.20.3

A

Using system B

151
Q

What system powers the normal brakes? 14.20.4

A

System B


152
Q

Is there a backup if hydraulic system B fails? 14.20.4

A

Yes. System A.


153
Q

Are autobrakes available using the alternate brake system? 14.20.5

A

No. They are only available with the use of the normal brake system

154
Q

Is antiskid available with the alternate brake system? 14.20.4

A

Yes. But antiskid is limited to wheel pairs instead of individual wheels. Also, locked wheel and touchdown protection is lost.

155
Q

Is antiskid protection available with the loss of both hydraulic sytems? 14.20.4

A

Yes

156
Q

When the AUTO BRAKES selector is positioned to RTO or one of the landing settings, if the AUTOBRAKE DISARM light illuminates briefly, is that normal? 14.20.5

A

Yes.

It is conducting a self-test.

157
Q

Extinguishing of the light indicates that the test was succesful What conditions are necessary in order to arm RTO?

A
  • On the ground 

  • Antiskid and autobrakes operational 

  • AUTO BRAKE select switch positioned to RTO 

  • Wheel speed less than 60 knots 

  • Forward thrust levers at idle
158
Q

With regard to RTO, what happens at 60 knots? 14.20.5

A

RTO activates 


159
Q

What happens between 60 and 90 knots if a takeoff is rejected? 14.20.5

A

The autobrake disarm light illuminates and autobraking is NOT initiated.

160
Q


What happens if the takeoff is rejected above 90 knots? 14.20.5

A

Autobraking is initiated when the thrust levers are retarded to idle.

161
Q

When will the autobrakes activate upon landing? 14.20.5 


A

Both thrust levers retarded to idle

Main wheel spin-up

162
Q


How can we disarm the autobrakes after landing? 14.20.6 


4 things

A
  • Moving the speedbrake lever to the down detent
  • Advancing the thrust levers after touchdown

  • Applying manual brakes

– Selecting to off

163
Q


When the flap handle is moved to position 1, what position do the leading edge flaps and slats move to? 9.20.14

A
  • Leading edge flaps to the extended position 


- Leading edge slats to the intermediate position

164
Q

At what flap selection are the slats in the fully extended position? 9.20.14

A

Beyond 5 


165
Q

Do we have any sort of flap load relief on the 737? 9.20.14

A

Yes.

When the flaps are set at 40 degrees, the flaps will automatically retract to 30 if airspeed exceeds 162 knots, and will re-extend when speed is reduced to 157 knots. 


166
Q

What is the autoslat system? 9.20.15 


A

With flaps selected to 1, 2, and 5, autoslats will automatically drive the slats to the fully extended position if the aircraft approaches a stall

167
Q

What is the function of the power transfer unit? 13.20.3

A

The power transfer unit supplies the additional volume of hydraulic fluid needed to operate the auto-slats and leading edge flaps and slats at the normal rate when the system B engine-driven hydraulic pump volume is lost. The PTU uses system A pressure to power a hydraulic motor- driven pump, which pressurizes system B hydraulic fluid.

168
Q

When will the PTU operate? 13.20.3-4

A
  • airborne 

  • system B engine-driven pump hydraulic pressure drops below limits 

  • flaps are less than 15, but not up 

169
Q

Is there an alternate means of extending the flaps and slats? If so, how does it function? 9.20.15

A

Yes.

The trailing edge flaps can be positioned electronically using the ALTERNATE FLAPS switch. The leading edge flaps and slats can be extended using power from the standby hydraulic pump, but cannot be retracted once they are extended

170
Q

When will the auto speed brake system operate on landing? 9.20.12 


A
  • SPEED BRAKE lever in the armed position 

  • SPEED BRAKE ARMED light is illuminated 

  • Both thrust levers at IDLE 

  • Main landing gear wheel spin up
    – flight spoilers deploy 

  • Right main gear strut compression
    – ground spoilers deploy
171
Q

When else will the auto speed brake system operate? 9.20.12 During an RTO when: 


A
  • Wheel spin up great than 60 knots 

  • Both thrust levers moved to IDLE 

  • Reverse thrust is selected 

172
Q

What happens when the APU fire switch is pulled? 8.10.2 


A
  • Arms the APU extinguisher circuit 

  • Closes the APU fuel shutoff valve, APU bleed air valve, and APU inlet door 

  • Trips the generator control relay and breaker
  • Allows the APU fire switch to rotate 

173
Q

How many APU fire bottles are there?

8.10.2

A

One

174
Q

How many loops are in the APU fire detection system? 8.20.3

A

One 


175
Q

What happens when you pull the engine fire switch? 8.10.2

A
  • Arms one squib on each extinguisher 

  • Closes fuel, hydraulic, and engine bleed air valves 

  • Deactivates the engine driven hydraulic
    pump LOW PRESSURE light 

  • Trips the generator control relay and breaker 

  • Disables thrust reverser 


`- Allows the engine fire switch to rotate 


176
Q

How many loops are in the engine fire detection system? 8.20.1

A

Two 


177
Q

How many engine fire bottles are there? 8.20.2

A

Two 


178
Q

What bus is engine and APU fire detection on? 8.20.1, 8.20.3

Extinguishing? 8.20.1, 8.20.3

A

Battery bus 


Hot battery bus 


179
Q

What are we testing with the Extinguisher TEST switch? 8.10.1

A

The circuitry, not the bottles themselves

180
Q

How many fire bottles are there for the lower cargo compartments?

A

One 


181
Q

Is the airplane equipped with fire suppression equipment for the main cargo compartment? 8.20.6

A

No 


182
Q

Will the master fire warning light illuminate and the fire warning bell sound if smoke is detected on the main cargo deck? 8.20.5

A

No


183
Q

What are your indications that there is a fire on the main cargo deck? 8.20.5

A

Both CARGO SMOKE lights illuminate and the associated smoke detector light(s) illuminate 


184
Q

What two different ways do we have to close the engine fuel shutoff valve in the wing leading edge? 7.20.4 


A

The engine fire switch and the engine start lever can both be used to close the engine fuel shutoff valve.

185
Q

What controls the MEC fuel shutoff valve? 7.20.4

A

The engine start lever. 


186
Q

When will the takeoff warning horn sound? 15.20.6

6 items

A
  • Trailing edge flaps not in the flaps 5 to 15 takeoff range, or 

  • Leading edge devices not in takeoff position, or 

  • Speed brake lever not in the down detent 

  • Stab trim not in the takeoff range 

  • Parking brake set 

  • Main Cargo Deck Door not properly closed, latched, and locked
187
Q


We’re cleared for takeoff, advance the engines, see them stabilize at 40%, and then press TO/GA. What will the flight directors do at that point? 4.20.5 


A

Command 10 degrees nose down.

188
Q

What will happen at 60 knots? 4.20.5

A

The FDs will command 15 degrees nose up until after liftoff and a sufficient climb rate is acquired, then they will command MCP speed plus 20 knots

189
Q


What if you forgot to turn on your flight directors?

Can you turn them on without reaching for the FD switches? 4.20.5

A

Yes. After 80 knots, and below 2,0000 feet AGL, and prior to 150 seconds after lift-ff, the FDs can be displayed by pressing TO/GA (flight director popup) 


190
Q

At what speed will the A/T mode annunciate THR HLD? 4.20.11 84

A

84 knots

Initial SAI 737-800 (NO 400) (26 decks)

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