Leading Edge Devices Flashcards

Question 1

Q

Leading Edge Devices

Answer

A

Flaps 1 - All Leading Edge devices with go out.

Kruger flaps -
Extend or not

Slats
4 x Slats
700 Flaps 1,2, or 5 - Extend - Amber / Green
Past Flaps 10-40 - Extended

800 Flaps 1-25 Extend

Contrast 700 / 800
4 x leading edge slats

Limitation
Holing in icing conditions prohibited
stat # 4 not anti-iced
No asymmetry protection

Question 2

Q

IRS Display and Mode Selector Unit

Answer

A

Test Function - 8 seconds / show faults
TK/GS - Track / Ground Speed - True
PPOS - Lat / Long
Wind - 100Kts
HDG/STS -

STS - How long until aligned -count down -
DU Ground Sky / numbers on arc / 
Align light will go out. 
- Equator - 4 min
- 76 N - 17 Minutes
- Dallas - 8 min

SYS L and R

Question 3

Q

IRS Display and Mode Selector Panel (cont)

Answer

A

Dual Channel Lights -
Won’t light unless both fail
button [overhead] - 1 x fail light

Loses it’s way
Update position - execute within 5 minutes
30 minutes on single battery

GSPAM

GPS - light flashing Didn't tell me / Lied to me / or abused me - White alignment light. 
Align - 
Steady - aligning or shutting down
Flashing - alignment cannot be completed
Lied to me, abused me, Didn't tell me

Fault - amber - fault detected

ON DC light -
power source switched to DC - switched hot battery bus.
Power from AC standby bus or AC transfer bus 2 was not normal.
horn from wheel well sounds to announce battery drain.
Momentary illumination during self test.

DC fail light
DC power to IRS not normal

IRS Mode selector
OFF
Alignment lost
all electrical power removed
Align
OFF to Align initiates alignment
Nav to Align updates alignment and zeros Ground Speed.
NAV (detected position)
enters Nav mode after the alignment of the cycle and entry of present position.
In NAV mode all IRS info available to airplane systems.
ATT
attitude and heading information only
attitude flag in view (attitude invalid) until align light extinguished.
heading flag in view( Heading invalid) until actual magnetic heading is manually enters after align light is extinguished.
Position and ground speed info not avail until the IRS is aligned on the ground.
Selector must be OFF before reselecting ALIGN or NAV.

Speed Trim -

PSEU

Auto Slats

Mach Trim

Question 4

Q

Service interphone with and dome light control

Answer

A

Exterior panels allow ground personnel to speed with cockpit.
OFF - External jacks deactivated
comm between FA’s still possible
ON - Add external jacks to inter phone system.

Dome Light -
One of the two lights on the captains side is connected to the hot battery bus.

Question 5

Q

Dome Light

Answer

A

Two Dome lights
One has two lights
One of them will always work off the hot battery bus.

Question 6

Q

Jack Box (Jumpseat audio panel

Answer

A

Left ALT
Switches Capt’s comms.
Can’t make PA

Right Alt
Switches FO comms to Alt sys.

V,B, R
Voice, Both, Range

Question 7

Q

Engine Panel

Answer

A

Reverser Light
10 Seconds fine

12 seconds -
1 not stowed - Light -
Auto re-stow circuitry triggered
Master Caution - Auto re-stow circuitry triggered

1) Isolation Valve thrust reverser control valve not in commanded position
2) 1 or more Thrust Reverser Sleeve not in commanded state.
3) Failure in sinc shaft lock circuitry

Question 8

Q

EECs

Answer

A

Electronic Engine Control
Channel A and B

changes channels after every flight
76% thrust trigger
Switch channels automatically with system failure

Light ON
Soft Alternate
Snap shot of current operating conditions

Check MEL for continued use after landing.

Don’t do anything
TOD
Throttles to Idle

Hard Alternate automatic

QRH
Put both in Hard Alt

Hot / Hung / Wet Start protections
Hot  - 725 / shut off at 670
Normal / Soft / and Hard N1 and N2 overspeed protection. 
Don't want to overspeed. 
Reduce power on each engine. 
push glass button put in Hard ALT

Operates in variety of conditions.
Hard - Settings in Hard ALT likely correlated to Thrust Lever position.
Normal - settings correlated to atmospheric conditions.
Soft - Snap shot of last functional engine setting

Question 9

Q

Crew Oxygen

Answer

A

AOM 16.1.1
Rules of thumb - 
4 x pax 1000 psa
3 x pax 750 psi
2 x pax 650 psi

14,000 masks out
12 minutes

114 cu ft bottle

Light on
Move switch to ON

Forces any passenger oxygen masks that didn’t deploy
to drop.

Question 10

Q

Broadband control panel

Answer

A

1 - minute amber
ON auto at 10,000 ft.
OFF at 7,000

Question 11

Q

Flight Recorder

Answer

A

Test - False oil pressure
Engines off
will sense APU Pressure and record.

Question 12

Q

Mach Airspeed warning

Answer

A

Test - No 1 / No 2

won’t test
Kruger flaps not re-stowed
two actuators on each side

Less than 4 minutes since start.

Slats on B system

Question 13

Q

Stall Warning

Answer

A

Stick shaker on each control column

Vibrate both sides.

Question 14

Q

PSEU Light

Answer

A

Ground Light

Proximity switch Electronic Unit
 Monitors 
	-Take off Config
	-Landing Config
	-Air/Ground sensing
	-Landing Gear
	-Door Lights

PSEU light on 

- fault in the PSEU 30 
- Over-wing exit door probably didn't unlock

In Flight - PSEU Light inhibited

Question 15

Q

Viewers - Gear Lights

Answer

A

If any set shows 3 green, likely safe to land

Question 16

Q

Flight Control panel

STBY RUD Switches

Answer

A

Flight control to off - Closed Flight Control shut off valve
Turned on Standby rudder shutoff valve

Disables low pressure light

Allows standby hydraulic pressure - starts coming on-line

rudder
thrust reverser

Master Caution - Flight Controls

standby rudder light on.

Shut off the - right
- shuts off flight control shut off valve. 
deactivates 
aileron
elevator
elevator feel

Question 17

Q

Flight Control Panel 
Alternate Flaps (guarded switch)

Answer

A

Red guarded Switch

Standby hydraulic pump - ON
ARM Alternate Flap Exertion switch
Close trailing edge flap bypass valve.
Extend trailing edge flaps with electric motor,

In Arm
Down 1st press
- Leading edge devices are coming all the way out, extended, hydraulically.

Down 2nd press
- Press and hold to allow electric motor to extend flaps to 15. Note: the motor can extend flaps full, but QRH recommends 15 for go around possibility.
2 minutes to extend.

UP - Latched up.

B - System failure
Using stand by hydraulic for leading edge devices
and electric motor for flaps.

Question 18

Q

Flight Control Panel

Spoiler switches

Answer

A

Maintenance function

Question 19

Q

Flight Control Panel

Low quantity - Light

Answer

A

half full will illuminate

Question 20

Q

Flight Control Panel

Low pressure Light

Answer

A

on momentarily with stand by hydraulics on

hopefully goes off when it comes on-line

Question 21

Q

Flight Control Panel

SBY RUD ON - Light

Answer

A

Light On when A or B STBY RUD selected

Means Stand by hydraulic pump is on.

Question 22

Q

Flight Control Panel

Feel Dif pressure light

Answer

A

On with 25% difference in pressure.
Light will be on with one engine started.
A of B on 3000 lbs of pressure

pitot tubes on each side of vertical stabilizer
rips off, will get light

Question 23

Q

Flight Control Panel

SPEED TRIM FAIL - light

Answer

A

Two lists

Low gross weight
high power
aft CG
Autopilot not on.

Speed trim tries to return aircraft to normal state.

turn at 4K’ no autopilot - speed trim activates

Speed Trim ARM
list 2
-100 to .60 fade to zero at .68 Mach
-10 seconds after take off
-5 seconds after last trim input
-autopilot off 
- sensing trim input needed

Question 24

Q

Flight Control Panel

MACH TRIM FAIl - Light

Answer

A

Speed increases
Center of lift moves aft
Nose heavy

Prevent mach tuck
light on is the only way you know its not working
.615
QRH - speed limit.

Question 25

Q

Flight Control Panel

AUTO SLAT FAIL - Light

Answer

A

Stall protection feature.

1,2,5 - extend / intermediate position - slats extend

auto slats come out automatically - pre-stall to keep plan from stalling

Stall protection
-Speed Trim 
-Auto Slats
-SMYD - Stall management yaw damper - Limits rudder to smaller control inputs to reduce likelihood of rolling. 
-Elevator feel shift 
Twice as hard to pull back vs pushing forward
-Stall warning 
-Stick shaker

Don’t stall swept wing airplane
System B

Lose B

PTU - A system pressure through motor pump to extend slats for System B
PTU transfers Power from A to B system

crisis over - slats return

Landing Gear Transfer Unit
Transfers powers and fluid from B to A system

B Pressure and quantity transfers to A to retract and extend landing gear.

If we lose A, B pressure and quantity will get the gear up.

Question 26

Q

VHF Nav, GPS, FMC switches

Answer

A

Selecting 1 or 2 will command all DU’s CA and FO to operate from selected switch.

One DU can run all DU’s

DU2 example - Hydraulic pressure showing nothing. Switch
amber - CDS fault - One DU has fault.

On 2 - if blank
everything goes on 1.

Question 27

Q

Fuel

Answer

A

Center tanks 28.8
Wing tanks 8600
46,000 lbs

800
35,000 lbs
10,900 lbs wings

800

6 drip sticks on each wing tank
4 drip sticks on each center tank

Classic

5 drip sticks on each wing.
None on center

Question 28

Q

Spar Valve

Answer

A

Hot battery Bus

Question 29

Q

Engine Valve

Answer

A

Battery Bus

Question 30

Q

Fuel Temp

Answer

A

#1 tank sensor
Limitation:
-49
-37
more than 1000 lbs in center tank. 
Mains must be full
Weight and Balance

Must have 2000 lbs to turn on center tank pumps

If both fuel pump low pressure lights come on, must turn center tank pumps off.

Southwest policy - One off, = Both Off.

Climbing or descending - turn on off
Scavenge Pump off - transfer slow rate / loaded flow

Center tank low pressure light. Pump off
scavenge pump continues pumping.

Center tanks pumps on -
Must monitor lights

total electric failure
fuel tanks - all have electric pumps

suction feed not guaranteed above 30K”
Don’t pull throttles to idle it will break suction and have duel engine failure

Two pumps off in One Tank - Master Caution.

Question 31

Q

Filter Bypass Light

Answer

A

Impending bypass - may have already bypassed.
if light 2 comes on.
Contaminated fuel, land immediately.

Limitation on fuel balance
1000 lbs

Question 32

Q

Fuel limit

Answer

A

Config
amber
1600 lbs center tank - no pressure - light will be on
Turn on center tank pump light extinguishes

One engine running

800 lbs quit telling you anything

2000 lbs - low fuel light
1675 lbs - low fuel - heat exchangers coolant or hydraulic

Question 33

Q

Can you Fuel the aircraft with No battery

Answer

A

Yes, open fuel panel, Manual fueling

elongated button, 50 lbs of pressure, fuel it by the stick.

Question 34

Q

Hot battery Bus

Answer

A

fire extinguishing capability
compass light
IRU’s
APU starter

ON -

Hot Battery Bus
Battery Bus
Switched Hot battery Bus
AC Standby Bus
DC standby Bus

30 minutes

Total failure - Write down when it happens.
Standby-by power

Battery Discharge Light

In flight - very concerned

Question 35

Q

TR unit

Answer

A

Have to check individual TR’s
Remote control - watch channel you want to watch.
Ground Light - DC or standby power

Question 36

Q

Battery

Answer

A

ON or OFF

Question 37

Q

Galley Power

Answer

A

On or OFF

Load Shed - Galley Shed

Question 38

Q

Standby power OFF

Answer

A

AC standby Bus off
DC standby Bus off
Battery Bus OFF

2 and 3 or 1 of 3 is OFF
load shed

What makes it come on?
no pressure on transmission

Question 39

Q

IDG’s light why? red guarded switches

Answer

A

Cannot reconnect in flight if red guarded switch is clicked off

Overheat
pressure fell - light comes on
drive torn up.

temp gauge -

Question 40

Q

stand by power in (AUTO) / Manual / ON

Answer

A

Auto
DC bus 1 or AC transfer Bus Fail
auto standby bus

manually disconnected
AC Standby bus / DC standby bus.
light on

On
Manually put into standby
30 minutes of power.

Question 41

Q

Ground Power

Answer

A

Ground power of good quality available.

Question 42

Q

Fuel Control Panel

Answer

A

Engine Valve
Spare Valve
Fuel Temp indicator
Crossfeed Valve Open Light (blue)
Filter bypass Lights (amber)
Crossfeed selector
Fuel Pump switches
Main Tank Fuel PUMP LOW PRESSURE Lights
Center Tank Fuel Pump Low pressure Lights

Question 43

Q

Engine Valve (light) Closed (ENG VALVE CLOSED) & SPAR VALVE CLOSED

Answer

A

Blue - extinguished - related engine or spar fuel shutoff valve is open.
Bright - Related engine or spar fuel shutoff valve in transit, or valve position and engine start lever or engine fire switch disagree.
Dim - related engine or spar fuel shutoff valve is closed.

Question 44

Q

Fuel Temp Indicator

Answer

A

Indicates temp in tank #1

Question 45

Q

Crossfeed Valve Open Light (blue)

Answer

A

Extinguished - Crossfeed valve is closed

bright - Crossfeed valve is in transit, or valve position &is selector disagree
dim - Crossfeed valve is open

Question 46

Q

Filter Bypass Light (amber)

Answer

A

Extinguished - fuel filter operating normally

Illuminated - impending fuel filter bypass due to contaminated filter

Question 47

Q

Crossfeed Selector

Answer

A

Crotrols fuel Crossfeed valve
Closed - isolates engine No1 and No2 fuel feed lines
Open - connects engine No1 and No2 fuel feed lines

Question 48

Q

Fuel Pump switches

Answer

A

ON - Activates fuel pump

OFF - deactivates fuel pump

Question 49

Q

Main Tank Fuel Pump Low Pressure Lights (amber)

Answer

A

Illuminated - fuel pump output pressure is low, or fuel pump switch is OFF
Note: two LOW PRESSURE lights illuminated in same tank illuminate Master Caution and FUEL system annunciation lights.
One LOW PRESSURE light causes MASTER CAUTION and FUEL system annunciator lights to illuminate MASTER CAUTION light recall.
Extinguished - fuel pump output pressure is normal.

Question 50

Q

Source off (light)

Answer

A

APU - ON

power available, it’s just not on the BUS.

Question 51

Q

Transfer Bus OFF - light

Answer

A

Means exactly what it says.

Question 52

Q

Transfer BUS AUTO (2 functions)

Answer

A

AC and DC function

AC - BUS tie breakers that will automatically pick up AC power if the other side of the BUS tie goes dead.
AC Bus 1
AC Bus 2

DC - Cross bus tie relay, when you intercept the glide slope, the relay separates the systems to ensure an ILS can be accomplished if there is a single electric failure. If it failed on the glide slope, a single electrical failure would make you inoperative.

OFF - Disables the AC and DC busses.

Question 53

Q

APU’s

Answer

A

Can start APU at 41,000
Limitations 
41,000
Bleed - 17,000
Bleed and Electric - 10,000

Available immediately
book says 1 minute
Southwest policy - 2 minutes.

Question 54

Q

Maint Light (APU)

Answer

A

Probably Oil 
Could be other things
Oil pressure 
760 start 
710 continuous

Question 55

Q

Fail safe APU - Automatic On-Line

Answer

A

If all power coming from APU and zero power coming from IDG’s

If power cut from the APU - Computer assumes that is not a desired electrical state.

Question 56

Q

APU shut down Auto

Answer

A

Limitations
Oil pressure 
fault
overspeed
fire

Question 57

Q

Flight Control Limitations

ALTERNATE FLAPS selector switch

Answer

A

No Speed brake below 1,000’
Don’t pull speed brake past flight detent
No speed brake and flaps at the same time

Alternate flaps selector switch

Alt Flaps - 0 to 15 then 15 to 0, then wait (5) minutes.
Changing directions - wait 15 seconds

2 minutes to reach Flaps 15

215 amps max load ground
wait 30 seconds after turning IRU’s off to turn AC power off. IRU’s are going through shutdown sequence.

Question 58

Q

Equipment Cooling

Answer

A

Horn - interrupted on the ground
ALTN with in 5 seconds.
Supply fan and exhaust fan

Question 59

Q

Emergency Exit Lights

Answer

A

Trigger

DC BUS fails
AC power removed

How long on? As long as the battery pack lasts

Question 60

Q

No Smoking switch

Answer

A

ON when in the aircraft

Question 61

Q

Auto seat belts

Answer

A

AUTO - OFF when landing gear and flaps are up.

AUTO - ON - Flaps out, or landing gear down which ever is first

Question 62

Q

Engine Start Switch

Answer

A

1 AC Transfer Bus igniter

Always start right side
Two igniters
AC standby igniter

Question 63

Q

Anti-ice systems - Window Heat panel - Overheat lights

Answer

A

OVHT Test
Power Test - All lights should come on

Limits
1 L, 2L, 3L, 1R, 2R, 3R,

3rd window not heated

Question 64

Q

Flight Controls Panel
Force Fight Monitor
2 x Auto
3 x Manual

Answer

A

Manually:

A - Flight control switch to Standby Rudder
B - Flight control switch to Standby Rudder
Alternate Flaps ARM

Automatically
1. Loss of system A or B, Flaps extended, airborne or wheel speed - 60kts,
2. Force Fight Monitor - Trip
a - Jammer disconnect - standby system kick non working system out, and works with good one.
b. Opposition - kicks both non working systems out and works alone.

Answer 65

A

Bleeds
Wing
Cowls
Heated windows
Windshield wipers

Answer 66

A

Illuminated - fuel pump output pressure is low and FUEL PUMP switch is ON
Note:

Answer 67

A

OVERHEAT - Amber - overheat condition is detected
Note: OVERHEAT lights illuminate if electrical power is interrupted.

2. Window Heat ON LIGHTS
Illuminated Green - Window heat is being applied to selected windows.
Extinguished when:
- Switch is OFF
-Overheat is detected
-system failure has occurred
-system is at the correct temp

Window Heat Switches
ON - Window heat is applied to selected windows
OFF - Windows heat is not in use.
Window heat Test Switch (spring loaded to neutral)

OVHT Test - bypasses thermostat, turns all overheat lights on
Simulates overheat condition
PWR Test - Provides a confidence test

FO
SIDE: ON - OFF
FWD: ON - OFF

Temperature controller maintains window No1 and No 2 to ensure Maximum strength of windows in the event of a bird strike.

Answer 68

A

FOOT AIR Controls
Pull - supplies conditioner air to Pilots leg positions
WINDSHIELD AIR Controls
Pull - Supplies conditioned air to No.1 windows for defogging

Answer 69

A

WINDSHIELD WIPER Selector
PARK - Turns off wiper motors and stows wiper blades
INT - Seven second intermittent operation
LOW - Low speed operation
HIGH - High speed operation

Permanent rain repellent coating on windows.

Don’t turn on dry windows will scratch

Answer 70

A

Probe Heat Lights - Amber - Related probe not heated
Note: if operating on standby power, probe heat lights do not indicate system status
Probe Heat Switches
ON - Power is supplied to heat related systems
AUTO - Power is automatically supplied to A and B probers heat systems when either engine is running
TAT TEST Switch
Push - Electrical Power applied to the TEMP PROBE on the ground.

Pitot probe for standby airspeed is NOT heated when on standby power.

No indication on panel with standby power - Capt airspeed at zero - probably not working.

Answer 71

A

COWL Anti-Ice Lights
Amber - Overpressure condition in duct downstream of engine cowl anti-ice valve.
COWL VALVE OPEN Lights
Blue
Bright - related anti-ice valve in transit or anti-ice valve position disagrees with related switch position.
Dim - related cowl anti-ice valve is open
Extinguished - related anti-ice valve is closed
ENGINE ANTI-ICE Switches
ON -
- related cowl anti-ice valve is open
- Stick shaker logic is set for icing conditions
- FMC Vref is not adjusted automatically
- Green TAI indication show on the engine display
OFF
- related cowl anti-ice valve is commanded closed
- stick shaker logic returns to normal if wing anti-ice has not been used in flight
- Green TAI indication on the engine display extinguishes

Amber lights on COWL ANTI-ICE due to excess pressure in the duct leading from cowl anti-ice valve to the cowl lip

Cowl electrically controlled and pressure actuated.

Engine spooled up to Approach Idle.

Answer 72

A

Thermal Anti-Ice Indications (TAI)
Green - Cowl anti-ice valves open
Amber - Cowl anti-ice vale is not in position indicated by related engine anti-ice switch.

Answer 73

A

Wing Anti-Ice valve open lights
Bright - Related wing ai valve in transit or disagrees
Dim - wing ai valve open
Extinguished - wing ai valve closed
Wing Anti-Ice Switch
OFF - Wing anti-ice control valves are closed.
ON - (in the air) Wing ai valves open
Stick shaker logic set for icing. - after turned on - logic remains even if turned off.

ON - (On the ground)

Wing ai valve open if both thrust levers are BELOW takeoff warning setting and temp inside both distribution ducts is below thermal switch activation temp.
Control valve closes if forward thrust lever ABOVE takeoff warning setting or thermal switch is activated in either distribution duct. Switch remains ON
Switch trip OFF at lift off.

Answer 74

A

Flight deck window Heat
Windshield wipers
Probe and sensor heat
Engine Anti-ice system
Wing Anti-ice system

Answer 75

A

Reverser Lights (ATIS)

Auto Re-stow circuit has been activated
One or more Thrust Reverser is not in commanded position
Isolation valve or Thrust control valve not in commanded position
A failure is detected in the synchronization shaft lock circuitry

Answer 76

A

AIrcraft not dispatch-able
Inhibited in the air
Not inhibited on the ground when:
- Engine is operating
- below 80 kts
- Approximately 30 seconds after touchdown.

Answer 77

A

ON - white light:
-Normal EEC mode is selected
- Engine ratings calculated using sensed conditions
ON (Extinguished) - EEC manually selected to hard alternate
ALTN (amber light)
- EEC auto or manually been switched to Alternate mode
ON and ALTN together
- EEC auto switched to Soft Alternate mode

Answer 78

A

Two systems
One for flight deck crew
One for passengers
Portable oxygen cylinders forward and aft in the cabin for emergency use.

Answer 79

A

-3 types of masks
- Diluter demand masks and regulators with separate smoke goggles (some 700W)
- Full face mask with adjustable regulator, for normal, 100%, and emergency oxygen (some 700W)
- Automatic pressure breathing mask and regulator (800W)
Pressure breathing above 27,000
Oxygen for crew - single bottle
System 1850 psi
- 4 x pax 1000 psi
- 3 x pax 737 psi
- 2 x pax 600 psi
Passenger oxygen -
-oxygen generators at each service unit, distributed through 4 continuous flow masks at each psu.
- Each Lavatory has 2 continuous flow mask and oxygen generator

Answer 80

A

Gauge - shows bottle pressure
AOM 16.1.2 for required oxygen pressure
Gauge is electrically powered, BAT Bus with battery switch on.

Passenger oxygen system -
- Normal guarded position -
- 14,000 ft cabin altitude auto deploy
- ON - manual activation to electronically drop masks
PASS OXY ON light
- Illuminates if activated automatically or manually.

Answer 81

A

Orange Transit Lights - Any LE device is in transit

Answer 82

A

Related LE slats in intermediate position

Answer 83

A

Related LE devices are fully extended

Answer 84

A

Press - Tests all annunciate panel lights

Answer 85

A

Any LE device is transit
Any LE device is not in programmed position with respect to TE flaps.
2 or more LE flaps or slats have moved from their commanded position.
During alternate flap extension until LE devices are fully extended and flaps reach 10 (-700W) or 15 (-800W)

Answer 86

A

(-700W)
- Flaps 1,2,or 5
- All LE flaps extended and all LE slats in intermediate position
- TE flaps 10 through 40
- All devices fully extended
(-800W)
- TE flaps 1 to 25 ALL LE flaps extended and all LE stats in intermediate position
- TE flaps 30 and 40, all LE devices are fully extended

Answer 87

A

No holding
- Due to slats 1 and 8 not being heated for anti-ice / de-ice,
- No flaps above 20,000 ft
- Flaps hydraulic system B

Answer 88

A

Asymmetry and Skew detection / protection systems
prevent flap asymmetry and skewed deployment
command flaps stop move to upon detection

Answer 89

A

700W - flaps 30-40, if airspeed increase to 1kt above max Vfe, flaps automatically retract to next lowest setting.
800W - flaps 10,15,25,30,or 40 only, 1kt above max Vfe, flaps automatically retract to next lowest setting.

Answer 90

A

Autoslats - Hydraulic System B normally and Hydraulic System A as a backup.

In both 700-800 slats in the EXT position, and the aircraft sense an impending stall, slats are automatically driven to FULL EXT position.
Safe AOA slats return to commanded position.

Answer 91

A

TE flaps - electrically operated
ALTERNATE guarded switch moved to ARM position
ALTERNATE FLAPS position becomes active and controls and electric motor to extend and retract TE flaps.
WARNING - No asymmetry or saw protection provided

Answer 92

A

Hydraulic Al operated through standby hydraulic system

ALTERNATE FLAPS in ARM, momentary press of ALTERNATE FLAps position switch drives all LE devices to full extension.
LE devices cannot be retracted using the alternate system.

Answer 93

A

3 Hydraulic systems A, B, and Standby

If A and or B Lost, A or B systems capable of powering all flight controls with no loss in controllability.
Each system has fluid reservoir in the main wheel well area pressurized by the Bleed Air system.
Alternate System reservoir connected to B system for pressurization and servicing.
Refill @ 76% on the ground only

Answer 94

A

OVERHEAT Light

Electric hydraulic pump overheated
fluid used to cool and lubricate the electric driven pump has overheated
minimum of 1675 lbs of fuel is required in the main tank for pump cooling

Answer 95

A

Low output pressure of associated hydraulic pump

- Deactivated with activation of fire switch

Answer 96

A

ENG 1 &2

Engine driven pump six times fluid volume than electric pump.
OFF
energizes the blocking valve solenoid and routes fuel back to reservoir.
pump is still lubricated as pump continues to rotate as long as engine is running.
ON
Normal position
De-energizes blocking valve solenoid to allow pump pressure to the system.
- should remain on at shutdown to extend solenoid life.

ELEC 1 &2
AC Driven cross wired
ELEC 2 on System A -
ELEC 1 on System B- Cross bussed in the event of an engine failure

ON - 
Energizes the electric driven hydraulic pump
System A powered by AC transfer Bus 2
Systems B powered by AC transfer Bus 1
OFF
Electrical Power removed from pump.

Answer 97

A

Systems A components 
Landing Gear
Nose Wheel Steering 
Alternate Brakes
Ground Spoilers
Ailerons 
Rudder 
Elevator and feel differential 
Autopilot A
Flight Spoilers
Left Reverser
Flap Power Transfer Unit 
(PTU)

System B components 
LE and TE flaps 
Auto slats 
Yaw Damper
Alternate Nose Wheel Steering
Normal Brakes
Aileron
Rudder
Elevator Feel differential 
Autopilot B
Flight spoilers
Right reverser 
Landing Gear Transfer Unit (LGTU)

Answer 98

A

Standby Rudder Automatic activation with loss of A or B system in flight with flaps extended or the Force Fight Monitor Trips
Single electric motor-driven pump to power
Rudder
LE Flaps and Slats (Extend only)
Left or Right Thrust Reverser

-Standby Yaw Damper under manual reversion

Automatic operation when
- System A or B Loss AND
- Flaps extended AND
- Airborne - or wheel speed < 60 kts AND
- FLT CONTL switch A or B Hydraulic system ON
Automatic operation
- Activates STBY electric motor-driven pump
- Open SBY Rudder shutoff valve
- Allows the STBY system to power the rudder and Thrust Reverser
- Illuminates
  - STBY RUD ON Master Caution, and FLT CONT Lights

Note; 
Engine Driven Hydraulic Pump result in:
	- A system 20%
	- B system 0%
Electric Pump results in:
	- A system 0%
	- B system - minimal amount for Landing Gear Transfer Unit

Loss of Standby Fluid will drain system B to 72%

System A Flap PTU engages #2 engine driven pump low pressure hour alternate flap selection. (No fluid transfer) PTU’s only function is to operate auto slats with low system B pressure at NORMAL RATE under following conditions:

- Airborne
- Flaps < 15 (700) and not UP (800)
- Loss of system B pressure.

Answer 99

A

2 mains
1 nose steerable
Hydraulic power for retraction, extension and nose wheel steering

landing gear lights - illuminated - down and locked
- independent back up
- no viewing pots on NG
- redundant but separate set of indicator light on OH panel
- Gear is down and locked as long as one green indicator light is illuminated
- Normal gear extension
  Hyd pressure releases unlocks
  Hyd pressure /gravity/air loads extend gear
  Overcenter Hyd locks hold gear at full extension
  Nose wheel doors remain open while gear is down
- Manual Gear extension
  3 manual gear extension handles in floor of cockpit
  - May be used with gear lever in any position
  - 24 inches of pull releases gear up-locks and gear free falls into position.
  - Gear cannot retracted manually
- Landing Gear retraction
  - Brakes automatically stop main gear rotation during retraction
  - Main Gear held in place by mechanical unlocks
  - Rubber seals and oversized hubcaps complete fairing of outboard wheels.
    -NLG Retraction (Nose Landing Gear)
  - Retracted forward
  - Rotation stopped by snubbers
  - Held in place by over center lock
  - Enclosed by doors linked to gear.
- Hydraulic pressure removed from system when LG lever placed to OFF.

Landing Gear Transfer Unit

- Supplies volume of hydraulic fluid Ned to operate the LGTU when: 
	- Airborne
	- Engine #1 RPM drops below limit value
	- Landing gear lever is positioned up.
	- MLG is not up and locked.

Answer 100

A

Normal Hydraulically powered Rudder and digital yaw damper system.

- Rudder is controlled by A and B if both systems fail
- Rudder can be manual positioned with peddles 
- above 135 kts pressure reduced by 25% to limit full rudder authority

Answer 101

A

Must use center tank to depletion followed by wing tank
1,000 lbs may remain in center provided balanced
Tank quantities
- wing tanks 8,600 + 8,600 = 17,200
- center tanks 28,800
- total = 46,000

Answer 102

A

-37º C to +49º C

Answer 103

A

Center tank depletion then wing
1,000 lbs retained in center tank
- Wing tanks must be full if the center tank quantity greater than 1,000
- Center tanks pumps must not be on unless personnel on the flight deck to monitor low pressure lights
- Center fuel tank pumps must be ON for takeoff with more than 1000 lbs in the center tank.
- must NOT reset tripped fuel quantity, fuel pump, or fuel pump control circuit breakers

Answer 104

A

Bright
- Valve is in transit
- Valve position and engine start level or engine fire switch disagree
Dim
Related engine or spar fuel shutoff vale is closed

Answer 105

A

Indicates fuel temp in No1 tank.

Answer 106

A

Extinguished

Crossfeed valve is closed
Bright
- Valve is in transit
- Valve position and CROSSFEED selector disagree
Dim
- Crossfeed valve is open

Answer 107

A

IMPENDING fuel filter bypass du to contaminated filter

Answer 108

A

Control fuel Crossfeed valve
closed - isolates engine No1 and No. 2 fuel feed lines
open - connects engine No1 and No2 fuel feed lines

Answer 109

A

Fuel pump output pressure is low and FUEL PUMP switch is ON

Answer 110

A

Fuel pump output pressure is low or FUEL PUMP switch is OFF

Answer 111

A

Well display until the imbalance is rectified within 200 lbs

Answer 112

A

Derives motive flow from No1 FWD fuel pump

Automatically from center to No1 tank at half fuel, continues until tank empty

Answer 113

A

Shut of with Engine Fire Handles

Shut off with idle / cuttoff levers

Answer 114

A

Some aircraft have nitrogen generation system to pressurize the center tank with inert gas to prevent combustion of the air volume in the tank.

Answer 115

A

22 and 30 volts

Answer 116

A

BAT DISCHARGE
- with BAT switch ON, excessive discharge detected
TR UNIT
- on the ground
  - Any TR has failed
- in the air
  - TR1 failed or
  - TR2 and TR3 failed
ELEC
- Inhibited in the air
- fault exists in DC power system or standby power system.

Answer 117

A

Removes power from battery bus and switched hot battery bus with normal power sources available
Removes power from batter bus, switched hot batter bus, DC standby bus, static inverter, and AC standby bus when DC batter is only power source.

Answer 118

A

Provides power to switched hot battery bus
energizes relays to provide automatic switching of standby elec system to battery power with loss of normal power.
Galley Power Switch - Supplies power to galley’s and broadband satellite when AC transfer busses powered.

Answer 119

A

DRIVE

- IDG failure
- Engine Shutdown
- IDG auto disconnect due to high oil temp
- IDG disconnect through generator drive DISCONNECT switch.

Answer 120

A

Disconnect IDG if electrical power is available

- IDG cannot be reconnected in flight

Answer 121

A

One of more of the following busses are unpowered.
- Battery Bus
- AC Standby Bus
- DC Standby Bus

Answer 122

A

-AUTO - In flight or on the ground, and AC transfer busses powered
- AC standby bus is powered by AC transfer bus 1
- DC standby bus is powered by TR1, TR2, and TR3
- In flight or on the ground, and loss of all AC power.
- AC standby bus is powered by battery through static inverter.
- DC standby bus is powered by battery
- Battery bus is powered by battery
-OFF
- STANDBY PWR OFF light illuminates
- aC standby bus, static inverter, and DC standby bus are not powered
BAT
- AC standby bus is powered by battery through static inverter
- DC standby bus and battery bus are powered directly by battery.

Answer 123

A

3 phase, 115 volts, 4000 Hz (+Hz) alternating current.

GND POWER AVAILABLE
- Ground power is connected and meets aircraft power quality standards.
Ground Power Switch

Answer 124

A

TRANSFER BUS OFF (L and R)

- Related transfer bus is not powered.

Answer 125

A

SOURCE OFF
- No source has been manually selected to power the related transfer bus, or the manually selected source has been disconnected.

Answer 126

A

GEN OFF BUS (L and R)

- That side IDG is not supply power to the related transfer bus

Answer 127

A

Generator Switches
- Three position switch, spring-loaded to neutral
- OFF
  - Disconnects IDG from related AC transfer bus by opening generator circuit breaker.
- ON
  - Connects IDG to related AC transfer bus by disconnected previous power source and closing generator circuit breaker.

Answer 128

A

AUTO (Guarded Position)
- BTB’s operate automatically to maintain power to AC transfer busses from any operating generator or external power.
- DC cross tie relay automatically provides normal or isolated operation as required.
OFF
- Isolates AC transfer bus 1 from AC transfer bus 2 if on IDG is suppling power to both AC transfer busses.
- DC cross tie relay opens to isolate DC bus 1 from DC bus 2.

Answer 129

A

8 APU GEN BUS OFF

- APU is running but not powering a bus APU generator powering both AC transfer busses.

Answer 130

A

9 APU GEN switches

- OFF - 
	- APU generator powering both AC transfer busses
		- Moving a single APU GEN switch to OFF illuminates related SOURCE OFF light. APU continues to power AC transfer busses. 
	- Subsequently moving other APU GEN switch to OFF disconnects APU generator from tie bus and removes APU power from AC transfer busses. 
	- APU generator powering one AC transfer bus; IDG powering one AC transfer bus. Moving related APU GEN switch to OFF disconnects APU generator from tie bus and AC transfer bus. IDG powers AC transfer busses. 
- ON 
	- Neither AC transfer bus powered by IDG - Moving a single APU GEN switch to ON:
		- Connects both AC transfer busses to the APU generator
		- Disconnects external power, if connected
		- Opposite SOURCE OFF light illuminates until the other APU GEN switch is moved to ON. 
	- Both AC transfer busses powered by IDG’s - moving an APU GEN switch ON.
		- Powers the related AC transfer bus from the APU generator.
		- Other AC transfer bus continues to receive power from the IDG.

Answer 131

A

Max operating altitude -
41,000 - Electrical
17,000 - Bleed
10,000 - Bleed and Electrical
Fuel Supply - No 1 main tank - One No 1 main tank fuel pump on while running APU.
APU can Suction feed from No1 tank in the event of fuel pump failure. This is not recommended fro prolonged use.
Starting - With A/C on AC power, transfer bus 1 energizes the starter motor - With AC on DC power, battery power starts the APU - If the battery switch is moved to the OFF position with the APU running, it will shut down as the ECU is ties to the battery switch.
APU electric power output regulation - In flight with the APU as the sole source of electrical power, all galley busses and main busses are automatically shed. - On the ground the APU attempts to carry a full electrical load but will shed galley busses and main busses until the load is within limits. -.

Answer 132

A

MAINT - APU requires maintenance
- APU may still be used
  - Light is disarmed when APU switch is OFF

Answer 133

A

APU Exhaust Gas Temperature
- Displays APU EGT
  - EGT indicator remains powered for 5 minutes after shutdown.

Answer 134

A

OVER SPEED
- APU RPM limit has been exceed resulting in auto shutdown
- Overspeed shutdown protection feature has failed a self-test during a normal APU shutdown
  - Light extinguishes 5 minutes after APU switch placed to OFF - Light is disarmed when APU switch is in OFF position.

Answer 135

A

Fault
- A malfunction exists causing the APU to auto shutdown
  - Light extinguishes 5 minutes after APU switch placed to OFF - Light disarmed when APU switch is OFF position.

Answer 136

A

APU Switch
- OFF - Normal position when APU is not Running
  - While APU is running, moving the switch to OFF trips the APU generator off the busses if connected, and closes APU bleed air value. APU runs for 60 seconds for cool down.
  - APU inlet door closes automatically after shutdown.
- ON - Normal position while APU is running
- START
  - Momentarily placing the switch in START and releasing it to ON initiates the start sequence.

Answer 137

A

Equipment Cooling Panel
4 fans, 2 supply Normal and alternate - Supply cool air to flight deck displays and E&E bay.
2 Exhaust fans Normal and alternate - collect and discard warm air form the flight deck displays overhead and aft electronic panels, circuit breaker panel and E&E bay -
-Lights Amber
-OFF
- No airflow from selected cooling supply fan.

Answer 138

A

EMER EXIT Lights (guarded switch)
- OFF
  - Prevents emergency lights form operating if aircraft electrical power fails or is turned off.
- ARMED
  - All emergency lights illuminate automatically if electrical power to DC Bus 1 fails or
  - AC power is turned off
- ON
  - All emergency lights illuminate

Answer 139

A

NOT ARMED amber caution light
- Illuminates when EMER EXIT LIGHTS switch not in ARMED position
- Master Caution and Overhead Annunciators.

Answer 140

A

No Smoking sign
- INOP - permanently indicate smoking is not allowed
FASTEN SEAT BELTS
- OFF
  - FASTEN SEAT BELTS and RETURN TO SEAT signs illuminated.
- AUTO
  - FASTEN SEAT BELTS and RETURN TO SEAT signs illuminated when flaps or gear are extended and extinguish when flaps and gear are retracted.
- ON
  The signs are illuminated

Answer 141

A

Engine Start Panel

Engine Start Switches
- GRD
  - Open start valve
  - Closes engine bleed valve
  - Arms selected igniters on ground and both igniters in the air- release to OFF at starter cutout
- OFF
  - Ignition normally off
  - Both igniters are activated when engine start lever is in IDLE and:
  - Uncommanded rapid decrease in N2 occurs;
  - N2 is between 57% and 50% or; In flight - N2 is between idle and 5%
- CONT
  - Provides ignition to selected igniters when engine operating and engine start lever is in IDLE
  - In flight - provides ignition to both igniters when N2 is below idle and engine start lever is in IDLE.
  - Provides ignition to both igniters when engine start lever is in IDLE.
  - Use FLT when operating in moderate to heavy precipitation and / or turbulence.

Answer 142

A

Engine Start Panel

Ignition Switch
- IGN L
  - Engine #1
    - Powered off Transfer Bus 1
  - Engine #2
    - Powered off Transfer Bus 2
- IGN R
  - Engine #1
    - Powered off AC Standby Bus
  - Engine #2
    - Powered off AC Standby Bus

Answer 143

A

Microphone activated with AC power
Erase Switch
- push 2 seconds all 4 channels are erased
Test Switch - Push for 5 seconds
- Status lights flashes once
- tone heard through headset
Headphone Jack
Status
- Illuminated momentarily during TEST to indicate no faults detected

Answer 144

A

CABIN Altimeter (ALT) differential Pressure (DIFF PRESS) Indicator
- Inner scale - cabin altitude feet
- Outer scale - Differential pressure between cabin and ambient
- Max differential 9.1 psi
- two pressure relief valves open aft portion of the fuselage
- Normal differential 7.45 and 8.35 psi / excessive defined by 8.75 psi
Cabin Climb Rate
- Indicates Rate of Climb
- indicates rate of climb or descent in feet per minute
ALT HORN CUTOUT - Push
- Cuts out intermittent cabin warning horn
- HORN when cabin exceeds 10,000 ft.

Answer 145

A

Environmental Control Panel
- AIR MIX VALVE indicator - Indicates position of air mix valves in Auto or Manual mode.
- TEMP indicator - displays temperature select by AIR TEMP selector.
- AIR TEMP selector - Selects temperature for the supply duct (main distribution duct) or PASS CABIN (the passenger cabin sensor)
- Control (CONT) CABIN temperature selector - allows for automatic temperature control or manual control (air mix valves controlled manually, automatic temperature controller bypassed.)
- Passenger (PASS) CABIN temperature selector - allow for automatic temperature control or manual control (air mix valves controlled manually, automatic temperature controller bypassed.)

Answer 146

A

Bleed air by engines, APU or external air cart/source.
- Air conditioning
- Wing and engine thermal anti-icing
- engine starting
- Hydraulic reservoirs pressurization
- Water tank pressurization
Bleed 5th stage low pressure compressor, if needed 9th stage modulated open.
Isolation valve, engine 1&2 electrically activated and pressure operated
Isolations vale in Auto mode:
- closed when both engine BLEED switches are off and both PACK switches on AUTO or HIGH.
- opens automatically if either BLEED air or PACK is positioned to OFF (4 corner rule)
- Pack - off, auto, or high, auto mode, pack will regulate to high flow if only one pack is operating and flaps are up. Will operate in high mode if APU is operations on pack. (Both engine BLEED switches are OFF.)
- Recirculation Fan - reduces pack load and bleed air demand. In AUTO, the fan will be signaled on until either PACK is set to HIGH.
- PACK light - pack trip off or failure of both primary and standby pack controls. Valve sill drive to full closed and air is valve driven to full cold. Selecting a warmer temp (as per QRH) will reduce workload, and allow possible reset.
- WING BODY OVERHEAT light - left overheat will indicated bleed air duct leak in left engine strut, left inboard wing leading edge, left air conditioning bay, keel beam, or APU bleed air duct. Right overheat will be indicative of the same respective areas for the right side (excluding the keel beam and APU bleed duct.). This abnormally can not be reset.
- BLEED TRIP OFF - light - Excessive engine bleed air temperature or pressure. The associated bleed air valve will close automatically.
- The OVHT TEST will test both WING-BODY OVERHEAT circuits, which are sued to detect bleed air duct leaks.
- DUAL BLEED - Based on APU valve position and Engine bleed position. This is to advise the crew of possible situations that could back pressure the APU.
  - APU bleed air valve is open and engine No1 BLEED air switch is ON or
  - APU bleed air valve and isolation valve open and engine No2 bleed air switch is ON.
- RAM DOOR FULL OPEN - Indicates ram door in full open position.

Answer 147

A

Outflow VALVE position Indicator - Displays position of outflow valve
Flight Altitude (FLT ALT) - Selected flight altitude
Land Altitude (LAND ALT) - Selected landing altitude
Outflow Valve Switch - Used to control pressurization by manually opening and closing the outflow valve.
Pressurization Mode Selector - controllers automatically alternate every flight
- AUTO - System controlled automatically.
- ALTN - Automatic control using alternate controller
- MAN - System manually controller using outflow switch.
AUTO FAIL
- Single controller failure when ALTN light is also illuminated
- Dual controller failure when illuminated alone.
- Caused by
  - Loss of DC power
  - Controller fault
  - Outflow valve control fault
  - Excessive differential pressure (>8.75 psi)
  - Excessive rate of cabling pressure change (+ or - 2,000 ft / minute )
  - High cabin altitude (Above 15,800)
- OFF SCHED DESCENT
  - If aircraft begins descending before set TOC in FLT ALT, the aircraft will revert to landing at the departure landing field elevation. Must reset actual flight altitude and landing altitude.
- ALTN - Pressurization system operating in ALTN mode.
  - Pressurization mode selector in ALTN position
  - Both ALTN and AUTO FAIL displayed, single controller has failed and system switched to alternate mode.
- Manual - Pressurization system operating in manual mode.

Answer 148

A

Toggles flight path vector on the attitude indicator

Answer 149

A

Hydraulic system B
- 1. AUTO BRAKE DISARM SPEED BRAKE lever moved to down detent during RTO or landing
- Manual brakes applied during RTO or landing
- Thrust levers advanced during RTO or landing
- Except during first 3 seconds after touchdown.
- Landing made with RTO selected
- RTO mode selected on ground
- Illuminates for 1-2 seconds then extinguishes
- Malfunction exists in automatic braking system.
- Extinguished AUTO BRAKE select switch set to OFF.
- AUTO BRAKE armed

Answer 150

A

OFF - Autobrake system deactivated.

- Selects desired deceleration rate for landing
- Switch must be pulled out to select MAX deceleration 
- 1,2,3, or MAX
- RTO automatically applies maximum brake pressure when thrust levers are retired to idle at or above 90 kts

Answer 151

A

ANTI-SKID INOP - fault detected.

Answer 152

A

Fuel Flow switch

- 3 positions switch print loaded to RATE
- RATE - Displays fuel flow to each engine
- USED - Displays fuel flow since last reset
- RESET - 
	- Reset fuel used to zero
	- Displays fuel used for 1 second, runs down to zero, and then displays RATE.

Answer 153

A

AUTO
- Both N1 bugs set by FMC
- Displays reference N1 bugs at active N1 limit for A/T.
BOTH
- Both reference N1 bugs and readouts manually set by turning N1 set inner knob
1 or 2
- Respective N1 reference but and readout manually set by turning N1 set inner knob.

Answer 154

A

Show position of TE flaps
Provides asymmetry and skew detection
When a problem is encountered
- TE flap bypass valve closes
- Shows position of left and right wing TE flaps.

Answer 155

A

Red GEAR Lights
- Landing gear is not down and locked with either trust lever at idle and A/C below 800 ft.
- Related gear is in disagreement with LANDING GEAR lever position.
Green GEAR lights
- Related gear is down and locked Only one green GEAR down light needs to be illuminated per gear to be sure the gear is down. (Main overhead panel)
- Gear horn is deactivated with all gear down and locked.

Answer 156

A

Normal pressure - 3000 psi - Normal pre-charge pressure - 1,000 psi
Maximum pressure - 3,500 psi

Answer 157

A

A/P - P/RST Red switch light
- Flashes and sound tone:
  - Autopilot has disengaged (-700)
  - Autopilot engage attempt has been made and is unsuccessful (-800)
- Steady light
  - Stab out of trim below 800 ft on dual channel approach
  - ALT ACQ mode inhibited during A/P go around if stabilizer not trimmed for single A/P operation.
  - Disengage light test switch held in position 2 - Automatic ground systems test fails.
  - Steady amber when disengage test is held in position 1.

Answer 158

A

A/T P/RST Red Switchlight
- Flashing
  - Auto throttle has disengaged
- Steady
  - Disengage light test held in position 2
  - Steady amber when disengage test is held in position 1

Answer 159

A

FMC amber light

- An alerting message exists for both MCDU’s
	- Test switch is in position 1 or 2

Answer 160

A

Disengage light test
- TEST1
- Illuminates autopilot /auto-throttle disengage and F

Answer 161

A

Red Lights
- CABIN ALTITUDE - Illuminates when cabling altitude exceeds 10,000 ft - accompanied by and aural warning horn (same as take-off config warning horn) - Extinguishes when cabin altitude below 10,000
- TAKEOFF CONFIG - Activates if aircraft not configured correctly for takeoff.
  2 Amber lights
- SPEEDBRAKES EXTENDED (F/o side)
  - In Flight
    - SPEED BRAKE lever beyond ARMED position
    - TE flaps extended more than flaps 10 or
    - Radio altitude less than 800 ft
      -On Ground
    - SPEED BRAKE lever is in the DOWN detent
    - Ground spoilers are not stowed
    - Note: light doesn’t work with less then 750 psi in hydraulic system A.
  - Below G/S P. INHIBIT (CA and F/O side)
    - Below glide-slope alert
    - Push to inhibit when below 1,000 ft.
  - SPEED BRAKE DO NOT ARM (CA side)
    - Light deactivated when SPEED BRAKE lever is in DOWN position.
    - Indicates an abnormal condition of test input to the speed break load alleviation system when the flaps are raised or;
    - During landing, indicates wheel speed has dropped below 60 kts and speed brake lever is not in the DOWN position.

Answer 162

A

STAB OUT OF TRIM

- Operates only with autopilot engaged
	- Indicates autopilot not trimming stabilizer properly
	- 10 second delay to avoid nuisance warnings
	- Momentary illumination during large changes in trim requirements is normal. 
- If illuminated monitor to ensure it eventually extinguishes
- If illuminated and stab not trimming, off A/P, Ret rim and on A/P.

Answer 163

A

Controls six display screens
NORM is normal setting and incorporates automatic switching in event of a failure.
Outboard DU failure - PFD auto to inboard DU and outboard blank
Inboard DU failure, - inboard remains blank
MAIN PANEL DU switch - controls what is displayed on inboard DU
LOWER DU switch - Controls whether NORM, engine indications, or navigation display is show on the lower DU.

Answer 164

A

Annunciations regarding Heads Up Display

Answer 165

A

Alerts for potential conflicts with ground as well as windshear

5 ground proximity alerts
- excessive descent rate
- Excessive terrain closure rate
- Altitude loss after takeoff or go-around
- Unsafe terrain clearance when not in landing configuration
- Excessive deviation below ILS glide slope

Answer 166

A

Windshear Alers
- Two tone siren followed by WINDSHEAR aural and red WINDSHEAR warning on the attitude indicators
- WINDSHEAR AHEAD - radar detected windshear close to and directly ahead of the aircraft.
- Enabled during takeoff below 1,200 ft RA
- GO AROUND, WINDSHEAR AHEAD - windshear within 1.5 miles and directly ahead of the aircraft as detected by radar.
- Enabled on approach below 1,200 ft RA
- MONITOR RADAR DISPLAY - Windshear within 3 miles and ahead of the aircraft
- Enabled during takeoff and approach below 1,200 ft RA
- Radar automatically begins scanning for windshear when:
- Thrust levers set for takeoff even if engine is off
- Thrust levers set for takeoff or both oil pressure active and transponder is on
- in flight below 1,800 ft RA.
- Windshear predictive alerts may be manual activated by pressing the WXR button on the EFIS control Panel prior to takeoff.
- Warning Lights and Test Switches
- INOP amber light
-GPWS computer malfunction or power loss
- SYS TEST switch
- Push momentarily on ground
- Below G/S and GPWS INOP lights illuminate
- TERR FAIL and TERR TEST show on navigation displays
- PULL UP and WINDSHEAR alerts illuminate
- GLIDESLOPE, PULL UP, WINDSHEAR aural warnings
- Terrain display test pattern shows on ND’s
- CAUTION TERRAIN aural sounds and TERRAIN caution message shows on ND’s.
-

Answer 167

A

FLAP INHIBIT switch

- simulates flaps in landing configuration so that the TOO LOW FLAPS warning is inhibited.

Answer 168

A

GEAR INHIBIT switch

- Simulates gear down condition and the TOO LOW GEAR warning is inhibited

Answer 169

A

TERR INHIBIT switch

Inhibits look-ahead terrain (caution and warning) alerts and terrain display.

Answer 170

A

Limitations

- Do not sue below 1,000 feet
- Do not extend beyond the flight detent in flight
- Do not us speed brakes in flight unless the flaps are at zero
- DOWN (detent)
	- All flight and ground spoiler panel faired. 
- ARMED 
	- Upon touchdown the lever moves to the UP position and all flight spoilers extend
	- Ground spoilers deploy when the right gear touches down
	- Spoilers stow if either thrust lever is moved to more than idle thrust
	- Speedbrakes auto-deploy logic
		- Lever must be in ARMED position 
		- SPEEDBRAKE ARMED light on
		- Both thrust levers at idle
		- Main gear 60 kts or gear compression 
		- RA less than 10 ft.

Answer 171

A

FLIGHT DETENT
- All flight spoilers are extended to their max position for inflight use.
UP
- All flight and ground spoiler are extended to the max position for ground use.

Answer 172

A

Speedbrake Load Alleviation Feature

- Limits speed brakes to 50% during certain high gross weight / airspeed combinations. 
- If speed brakes are deployed to the FLIGHT DETENT they are automatically returned to 50% pint and handle moves to reflect actual position. 
- Speed brakes may be manually moved beyond 50% to override load alleviation protection, but will require more force and handle held in FLIGHT DETENT.

Answer 173

A

IDLE
- Energized ignition system through EEC
- Opens spar fuel valve
- Open engine mounted fuel shutoff vale
CUTOFF
- Closes both spar and engine fuel shutoff valves
- de-energizes ignition system
- note: 800 illuminate red in the event of engine fire or engine fire test.

Answer 174

A

MAIN ELEC
- NORMAL - Normal operating position
- CUTOUT - Stops the main electric trim inputs the stab trim actuator
AUTOPILOT
- NORMAL Normal operating position
- CUTOUT - Autopilot trip inputs are disconnected from the single stab trim motor.

Answer 175

A

Flap Limitations

- No holding in icing with flaps extended in any position.
	- due to slats 1 and 8 not being heated for anti-ice 
	- No flaps above 20,000
- Flaps Hydraulic system B
- Flap failure protections
	- symmetry and Skew detection / Protection systems
		- Prevents flap asymmetry and skewed deployment
		- command flaps to cease movement upon detection
	- Flap Load Relief System (Flap handle does not move)
		- With flaps set, once air speed increases to 1 kt above maximum flap extension speed, the flaps automatically retract to the next lowest setting.

Answer 176

A

Reverse thrust is for ground use only
Forward Thrust LeverS - cannot be advanced if the reverse thrust lever i sin the reverser deployed position
Reverse Thrust Lever - Cannot be selected unless the forward thrust levers are in the idle position.
- When deployed forward thrust revers are locked in idle position
- Reversers are electrically controlled and hydraulically operated (system A left thrust reverser, system B right thrust reverser)
- conditions to be me prior to activation of reversers
  - Battery switch on
  - Engine fire handle down
  - Air ground sensor on ground or RA less than 10 ft
  - NG 2 of 3 gear on the ground.

Answer 177

A

Disengages the A/T if engaged. A/T disengage lights flash until switch is pushed a second time. If A/T disengage on their own, pressing the switch one time will cancel flashing.

Answer 178

A

3 systems
- Engine overheat and fire detection powered by battery bus.
- Engine fire extinguishing powered by hot battery bus
Fire detection and extinguishing is available for (ALE) APU, Lavatory, and Engines
- Main gear has fire detection only (no extinguishing)
- Cargo Compartment has smoke detection and fire suppression systems

Answer 179

A

OVERHEAT DETECTOR loop switch
- Both engines have dual loop fire detection. Both must sense overheat or fire condition
  - ENG OVERHEAT light remains on until it drops blow the onset temperature
- overheat: both master cautions, OVHT/det system annunciator light, related engine overheat light.
- fire: fire warning bell, both master fire warning lights, related engine fire switch illuminates, and all related engine overheat alert indications illuminate.
  - On 800 related engine start lever illuminates
- switch description
  - NORMAL - detection loop A and B air active
  - A - loop A active
  - B - loop B active

Answer 180

A

BELL CUTOUT switch
- Pressing switch
  - Extinguishes both master warning lights
  - Silences fire warning bell
  - silences remote APU fire warning horn
  - Resents the system for addition warnings

Answer 181

A

2 x engine fire extinguishing bottles each has two squibs on it for redundancy.

Either bottle can be discharged into either engine.
APU single bottle with 1 squib.
Switch is used to test discharge circuitry for all 3 bottles.

Answer 182

A

FAULT /INOP (move left)
- Test the fault detection circuits for both engines and APU
- 5 totally lights : 2 master caution, ovht/det annunciator, fault light, APU det inop light.
OVHT/FIRE (move right)
- overheat and fire detection loops on both engines, APE and fire detector in the main wheel wells (AC power only are tested.
- 10 total lights, 11 if AC power is available (wheel well light), 12 on the 800 engine start levers.

Answer 183

A

APU FIRE switch
- APU in a fire proof compartment in the tail section.
  - Illuminated red- indicates fir in the APU and unlocks APU fire switch
  - IN - Normal position,, mechanically locked if no fire signal.
    - can be released with manual release mechanism
      -UP - F BAGI
      Fuel solenoid deactivated and sov closes.
      Bleed air valve closes,
      Arms squibs
      Gen control relay and breaker tripped
      Air inlet closes
      -Rotating left or right will discharge APU bottle.

Answer 184

A

ENGINE FIRE switch
- illuminated - indicates fire n related engine and Unlocks the related engine fire switch
- IN - normal position mechanically locked if no fire signal
- UP - FELT BAG
  - Fuel sov closed
  - Engine hydraulic sov closes
  - Low pressure light deactivated
  - TR deactivated
  - Engine Bleed air valve closed
  - Arms squibs
  - Gen control relay and breaker tripped
    - Rotating the handle electrically firs a squib, discharging the extinguishing agent into related engine. Rotating the other way discharges the other bottle.
    - The L or R bottle discharge light will illuminate a few seconds after it is rotated.

Answer 185

A

Illuminated indicates overheat in related engine

Answer 186

A

FAULT light amber

- Illuminated with OVHT DET switch in BOTH
	- Both engine detector loops have failed
- Illuminated w/OVHT DET switch in A or B
	- The selected engine loop has failed
- Also illuminates while testing Fault/INOP system

Answer 187

A

WHEEL WELL light
- Illuminated - indicates fire in the main gear wheel well. (AC power required)
  - No extinguishing capabilities

Answer 188

A

BOTTLE DISCHARGE light amber

- Illuminated - indicates related Fire extinguisher bottler has been discharged

Answer 189

A

APU DET INOP light (amber)

- Illuminated - indicates the APU fire detection loop has failed

Answer 190

A

APU BOTTLE DISCHARGE light (amber)

- Illuminated indicates APU extinguisher bottle has discharged

Answer 191

A

EXTINGUISHER TEST light (green) and switch
- illuminated - when the switch is positioned to 1 or 2, each bottle’s squib circuitry is normal.
- 10 total smoke detectors in the aircraft
  - 4 forward compartment
  - 6 aft compartment
- Smoke detectors are set up in 2 loops. 1 from each of the loops must detect smoke for warning.
- cargo bottle with provided 60 minutes of fire suppression

Answer 192

A

EXT test lights (green)

Illuminated Cargo fire test switch is pressed and bottle discharge squib circuitry is normal.

Answer 193

A

DET SELECT switches
- NORM - detection loop A and B active
- A - A active
- B - B active

Answer 194

A

DETECTOR FAULT light (amber)
- One or more of the loops in either cargo camp are ent failed
  - Using the DET SELECT switches you can identify bad loop.

Answer 195

A

Fire Protection and Extinguishing
4 TEST switch
- When pressed circuits for both forward and aft cargo compartments are tested

ARM Switches forward and aft
- when pressed, extinguishers for corresponding cargo compartment is armed
  - as installed (ETOPS)
    - If bottle discharged and system remain armed, the 2nd bottle discharge is inhibited upon landing.

Answer 196

A

Fire Protection and Extinguishing

Cargo FIRE warning lights (red) (forward and aft)
- Illuminated - at least one in each loop has detected smoke.
  - if one loop has failed, at least one in the remaining loop detects smoke.

Answer 197

A

DISCH light (amber)
- illuminated - indicates the extinguisher bottle has discharged
  - as installed (ETOPS) once the first bottle is discharged, times set for 60 minutes to discharge the 2nd bottle

Answer 198

A

Cargo Fire Discharge switch

- if the system is ARMED, the bottle with be discharged into the cargo compartment.

Answer 199

A

Heads UP Display control panel 
MODE - Selects desired mode
STBY - Selects standby mode
RWY - used to enter runway length for low vis takeoff operations
G/S - Used to enter glides slope angle 
	- FAULT amber light HIG BITE fault

Answer 200

A

Rudder Trim: AC motor repositions neutral point of rudder feel and centering devise
- changes runner trim indicator units left or right of neutral
- if no AC power you will see OFF on left side of indicator
- CAUTION: make use knob springs back to neutral prior to flight
Aileron Trim
- 2 switches must be used in tandem to make aileron trim activate
- No actual trim on ailerons, activating simply redefines neutral position of ailerons by providing constant input to PCU’s
- Aileron Trim switches also control spoiler mixer if enough aileron trim is used
- Hydraulic pressure is required for trim activation
- CAUTION: do not use aileron trim with A/P on. Very high rolling forces upon disconnection of A/P.

Answer 201

A

NORMAL - Normal ops of the control column cutout switches
OVERRIDE
- bypasses the column cutout switches
- restores power to the stab trim switches
- control column trim switches will work regardless of control column position.
- If stab trim is jammed, your may be up against the column cutout switch (opposite force)
- Use STAB TRIM OVRD switch to enable use of main electric stab trim again.

Answer 202

A

Two CFM 56-7 engines.
Dual rotor, axial flow turbofan,
N1 rotor
- low pressure compressor and low pressure turbine.
N2
- high pressure compressor and high pressure turbine.
N1 and N2 are mechanically independent,

N2 drives the engine gearboxes.
Bleed-air powered starter motor is connected to the N2 rotor.
Dual channel electronic engine control (EEC) regulates each engine.
EEC monitors auto-throttle and Flight Deck Crew Inputs to automatically set engine thrust.

Answer 203

A

Full authority digital EEC.
Two independent control channels with automatic transferring if one fails.
With each start attempt EEC alternates between channels.
EEC uses thrust lever input to automatically control forward and reverse thrust
N1 is used by EEC to set thrust in two control modes. Normal and alternate
Manual selection of the control mode can be made with EEC switches on the engine panel

Answer 204

A

Normal mode EEC uses sensed flight condition and bleed air demand to calculate N1.
EEC compares commanded N1 and adjusts fuel flow to achieve the commanded N1
Full thrust is available at a thrust lever position less then fuel rated take off
Fixed or assumed temperature derated takeoff thrust rating are set at thrust lever positions less than full rated takeoff.
Max thrust is available at forward stop.
EEC limits thrust according to aircraft models.
B737-700 CFM 56-7B24
B737-800 CFM 56-7B27

Answer 205

A

EEC has two alternate modes. Soft or hard.
If required signals do not allow normal mode. EEC automatically switches to soft alternate.
EEC ON light
Uses last valid flight conditions to define engine parameters. Causes no immediate change in thrust. Thrust ratings might occur as flight conditions change. Soft alternate will remain until manually selecting ALTN on the EEC switch.

Hard alternate is equal to or greater than normal thrust settings at the same thrust lever setting.
Soft alternate mode the ON indication remains visible. The ON light is blanked in hard alternate.

Answer 206

A

EEC provides N1 and n2 redline overspeed protection in both normal and alternate modes. The EGT must be observed by the crew because the EEC does not provide EGT redline exceedance protection.

Answer 207

A

EEC automatically selects ground minimum idle, flight minimum idle and approach idle.

In Approach Idle, The height percent RPM improves engine acceleration time in the event of a go-around. Approach idle is maintained until 2 seconds after touchdown, when ground idle is selected.

In flight if a fault prevents the EEC from receiving flap or ain’t-ice signals approach idle schedule beings below 15,000 ft MSL.