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747 SKV KALITTA > SKV > Flashcards

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1
Q

WHAT TURNS ON THE EMERGENCY LIGHTING SYSTEM?

A

LOSS OF DC POWER (BUS 4)

AOM Vol II pg 1-51 Airplane General

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2
Q

FULLY CHARGED EMERGENCY LIGHTING BATTERIES SHOULD PROVIDE LIGHT FOR HOW LONG?

A

15 MINUTES

AOM Vol II pg 1-51 Airplane General

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3
Q

WHAT IS THE WING SPAN OF THE 747-400?

A
  1. 5” Feet
  2. 4 Meters

AOM Vol II pg 1-1 Dimensions

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4
Q

WHEN ARE THE LANDING LIGHT AT THEIR MAX INTENSITY?

A

LANDING GEAR DOWN

AOM Vol II pg 1-28 Airplane General

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5
Q

WHAT IS THE PURPOSE OF FLIGHT DECK ACCESS LIGHTS?

A

TO GAIN ACCESS TO THE FLIGHT DECK WITH GROUND HANDLING BUS POWERED.

AOM Vol II pg 1-25. Airplane General

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6
Q

WHEN DO THE ‘NO SMOKING’ AND ‘FASTEN SEAT BELT’ SIGN AUTOMATICALLY ILLUMINATE REGARDLESS OF SWITCH POSITION?

A

WHEN SUPERNUMERARY OXYGEN IS ON.

AOM Vol II pg 1-18, also pg 1-49 Airplane General

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7
Q

WHAT IS THE ADVANTAGE OF SELECTING LWR ON THE BEACON LIGHT SWITCH?

A

WON’T FLASH DURING LOW VISIBILITY.

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8
Q

WHAT IS THE TURNING RADIUS WITH BODY GEAR STEERING ARMED?

A

153’ Feet
46.6 Meters

170” Feet without body gear steering armed

AOM Vol II, Airplane General

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9
Q

Where is the emergency equipment located on the BCF’s?

A

Bulkhead just forward of Left Upper Deck Door.

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10
Q

THE ESCAPE ROPE AT DOOR L1, IS LOCATED WHERE?

A

IN THE UPPER DOOR SILL.

AOM Vol II, pg 1-66 DOORS

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11
Q

BLEED AIR IS USED IN WHAT SYSTEMS?

A 
Bleed air can be supplied by the engines, APU, or a ground air source. 
Bleed air is used for: 
• air conditioning 
• pressurization 
• wing and engine anti–ice 
• engine start 
• leading edge flaps 
• aft cargo heat 
• cargo smoke detection
• hydraulic reservoir pressurization 
• potable water tank pressurization 
• air driven hydraulic demand pumps 
• thrust reversers

AOM Vol II, pg 2-34 Air Sytems

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12
Q

CAN THE APU PROVIDE BLEED AIR IN FLIGHT? UP TO WHAT ALTITUDE?

A

YES, FOR ONE PACK UP TO 15000 Feet

AOM Vol II, pg 7-36, Engines and APU

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13
Q

TURNING AN ENGINE BLEED AIR SWITCH OFF DOES WHAT?

A

If an Engine Bleed Air switch is off, the respective engine bleed air valve, PRV, and HP bleed valve are closed.
If a bleed air overheat is detected, the PRV and HP bleed valves close. Pushing an Engine Bleed Air switch from OFF to ON resets the engine bleed fault detection system.

Bleed air is available for nacelle anti-ice operation with the Engine Bleed Air switch ON except when:
• the PRV has failed closed, or
• the PRV has been closed due a bleed air overheat, or
• the start valve is not closed
Bleed air is available for nacelle anti-ice operation with the Engine Bleed Air switch off except when:
• the PRV has failed closed, or
• the PRV has been closed due a bleed air overheat, or
• the start valve is not closed, or
• the HP bleed valve is failed open
Bleed air is available for thrust reverser operation with the Engine Bleed Air switch either ON or off except when:
• the PRV has failed closed, or
• the PRV has been closed due a bleed air overheat, or
• the start valve is not closed

AOM Vol II, pg 2-34, Air Systems

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14
Q

IF THE BLEED SWITCH IS OFF IS NAC ANTI ICING AVAILABLE FOR THAT ENGINE?

A

YES, PROVIDED THERE ISN’T A FAULT PRESENT.

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15
Q

WHAT WILL ILLUMINATE THE SYS FAULT LIGHT?

A

BLEED AIR OVERHEAT, BLEED AIR OVERPRESSURE, HP BLEED VALVE OPEN WHEN COMMANDED CLOSED, PRV OPEN WHEN COMMANDED CLOSED.

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16
Q

WITH THE LIGHT (SYS FAULT) ILLUMINATED, IS REVERSING AVAILABLE ON LANDING?

A

NOT IF THE LIGHT IS ON DUE TO AN OVERHEAT.

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17
Q

WHAT UNIT IN THE BLEED AIR SYSTEM REDUCES BLEED AIR TEMPERATURE?

A

FAN AIR PRE-COOLER.

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18
Q

WITH A (L DUCT OVT), WHAT SYSTEMS ARE NO LONGER AVAILABLE?

A
  • WAI
  • DEMAND PUMP
  • HYD RESERVOIR PRESS
  • PACK
  • LEADING EDGE DEVICES (LED) WILL BE IN SECONDARY
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19
Q

APU BLEED AIR IS SUPPLIED TO WHICH DUCT?

A

CENTER SECTION OF THE BLEED AIR DUCT.

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20
Q

WHERE IS THE DUCT PRESSURE DISPLAYED?

A

PRIMARY EICAS AND ECS SYNOPTIC PAGE.

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21
Q

WHAT AREAS RECEIVE ANTI-ICE PROTECTION?

A
  • ENGINE NACELLE
  • WING
  • PROBE HEAT
  • WINDSHEILD
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22
Q

UNDER WHAT WEATHER CONDITIONS IS NAC ANTI-ICE REQUIRED TO BE ON?

A
  • WHEN THE OAT ON THE GROUND AND FOR TAKE OFF, OR TAT IN FLIGHT IS 10°C (50°F) OR BELOW, AND VISIBLE MOISTURE IS PRESENT. SUCH AS CLOUDS, FOG WITH VISIBILITY OF 1 MILE OR LESS, RAIN, SNOW, SLEET AND ICE CRYSTALS.
  • ON RAMPS, TAXIWAYS OR RUNWAYS WHERE SURFACE SNOW, ICE, STANDING WATER OR SLUSH MAY BE INGESTED BY THE ENGINES OR FREEZE ON ENGINES, NACELLES OR ENGINE SENSOR PROBES.
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23
Q

ARE THE TAT PROBES HEATED? WHEN?

A

YES, INFLIGHT ONLY.

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24
Q

WHAT INDICATIONS DO WE HAVE THAT NAC ANTI-ICE IS ON? WING?

A

NAI/WAI ICON DISPLAYED ON THE PRIMARY EICAS AND ECS PAGE.

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25
Q

WHAT SECTION OF THE WING IS ANTI-ICED?

A

LEADING EDGE WITH LE FLAPS RETRACTED.

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26
Q

AT FLAPS 5, WHAT PORTION OF THE LEADING EDGE IS BEING DE-ICED WITH WAI ON?

A

NONE.

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27
Q

WHICH WINDOWS ARE PROVIDED ANTI-ICE AND ANTI-FOGGING PROTECTION?

A

THE FORWARD WINDOWS HAVE EXTERIOR SURFACE ANTI-ICING, AND INTERIOR SURFACE ANTI-FOGGING PROTECTION. THE SIDE WINDOWS HAVE INTERIOR SURFACE ANTI-FOGGING PROTECTION ONLY.

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28
Q

WHEN IS ANTI-FOGGING AVAILABLE TO THE WINDOWS?

A

ANY TIME THE AIRCRAFT IS POWERED.

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29
Q

HOW DO WE RESET A WINDSHIELD HEAT CONTROLLER FLAULT?

A

TURN THE WINDOW HEAT SWITCHES OFF FOR 10 SECONDS THE BACK ON.

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30
Q

WHERE IS THE WINDSHIELD WASHER FLUID RESERVOIR LOCATED?

A

THE WASHER FLUID RESERVOIR IS LOCATED BEHIND THE DOOR IN THE BOOK STORAGE AREA ON THE CAPTAIN’S SIDE PANEL.

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31
Q

WHAT IS THE PURPOSE OF THE OBS AUDIO SYSTEM SWITCH, ON THE OVERHEAD PANEL?

A

CONNECTS OBS AUDIO PANEL TO EITHER CAPTAIN OR FO.

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32
Q

WHEN ILLUMINATED, WHAT DOES THE OFFSIDE TUNING LIGHT INDICATE?

A
  • THE RADIO TUNING PANEL IS BEING USED TO TUNE A RADIO NOT NORMALLY ASSOCIATED WITH THIS RADIO TUNING PANEL
  • THE RADIO NORMALLY ASSOCIATED WITH THIS PANEL IS BEING TUNED BY ANOTHER RADIO TUNING PANEL.
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33
Q

HOW MANY VHF RADIOS ARE INSTALLED?

A

3

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34
Q

WITH 121.5 SELECTED IN THE R VHF, CAN THE RECEIVER VOLUME CONTROL FOR THAT RADIO BE TURNED OFF?

A

NO

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35
Q

HOW CAN YOU MONITOR FOR AN “IM” SIGNAL DURING A CAT II APPROACH?

A

ON AUDIO PANEL, SELECT MKR AND PUSH VOLUME KNOB.

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36
Q

HOW CAN WE TUNE DATA IN THE C VHF?

A

DIAL PAST 136.000 OR BELOW 118.000 AND SELECT TRANSFER SWITCH.

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37
Q

HOW IS THE OXYGEN MASK OPERATION VERIFIED DURING PREFLIGHT?

A

SELECT FLT ON ACP, SPEAKER ON, SELECT PUSH TO TEST ON 02 PANEL ALONG WITH EMER KNOB, SIMULTANEOUSLY PUSH INTERPHONE SWITCH ON ACP.

ON 742-745, SELECT OXY ON THE AUDIO SELECTOR PANEL.

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38
Q

WHAT SHOULD BE SEEN WHEN PUSHING THE COCKPIT VOICE RECORDER TEST BUTTON?

A

PUSH TEST SWITCH AND OBSERE PULSATING INDICATIONS ON METER.

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39
Q

HOW MANY PTT SWITCHES ARE IN THE COCKPIT?

A

7-8 DEPENDS ON AIRCRAFT.

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40
Q

SELECTING THE SERV INTERPHONE SWITCH TO ON DOES WHAT?

A

PROVIDES VOICE COMMUNICATION BETWEEN GROUND CREW STATIONS AT VARIOUS LOCATIONS AROUND THE AIRPLANE.

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41
Q

WHAT DOES “IDG” STAND FOR?

A

INTEGRATED DRIVE GENERATOR.

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42
Q

HOW MANY AC POWER SOURCES ARE AVAILABLE TO THE AIRCRAFT?

A

8

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43
Q

WHAT TURNS ON AN IDG DRIVE LIGHT?

A 
H - HIGH
O - OIL
T - TEMPERATURE
L - LOW
O - OIL 
P - PRESSURE
UNCORRECTABLE FREQUENCY FAULT.
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44
Q

WHAT IS THE PURPOSE OF UTILITY BUSES?

A

TO PROTECT THE ELECTRICAL SYSTEM FROM UTILITY BUS FAULTS AND PROVIDES LOAD MANAGEMENT THROUGH AUTOMATIC LOAD SHEDDING.

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45
Q

WHAT BUSES ARE POWERED WITH # 1 & # 2 EXTERNAL POWER AVAILABLE BUT NOT ON?

A
  • GROUND HANDLING

- MAIN DECK CARGO HANDLING.

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46
Q

WHAT BUS NORMALLY POWERS THE SERVICE BUS? IS THERE AN ALTERNATE MEANS TO POWER THE BUS?

A
  • AC BUS 1 IS THE NORMAL SOURCE

- GROUND HANDLING IS ALTERNATE SOURCE VIA SWITCH AT DOOR 1L.

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47
Q

THE APU AND MAIN STANBY BUSES ARE NORMALLY POWERED FORM WHICH BUS(S)?

A
  • AC BUS 3 IS THE NORMAL SOURCE

- APU/MAIN HOT BATTERY BUS VIA INVERTERS

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48
Q

WITH THE LOSS OF #3 AC BUS, THE APU STBY BUS IS POWERED FROM WHICH SOURCE?

A
  • AC BUS 1

- APU HOT BATTERY BUS THROUGH INVERTER.

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49
Q

HOW CAN I ISOLATE THE #4 DCIR?

A

DE-SELECT #4 BUS TIE SWITCH.

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50
Q

WHAT WILL POWER THE CARGO BUS WITH #2 EXTERNAL AVAILABLE AND #2 APU GEN AVAILABLE?

A

2 EXTERNAL POWER.

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51
Q

WHAT IS THE MINIMUM OIL QUANTITY FOR DISPATCH?

A

16 QTS.

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52
Q

IF THE EGT LIMIT IS EXCEEDED WHAT IS INDICATED? ON TAKEOFF?

A

RED BOX/BAR AND A RED LINE WILL APPEAR

BUT WILL BE INHIBITED FOR 5 MIN AFTER “TOGA” IS PUSHED.

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53
Q

THE AMBER LINE ON THE N1 INDICATOR REPRESENTS WHAT?

A 
MAX N1 (EEC OVERBOOST PROTECTION)
ALLOWABLE THRUST AVAILABLE.
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54
Q

WHAT VALVES ARE CONTROLLED BY THE FUEL CONTROL SWITCH?

A

SPAR AND ENGINE VALVES.

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55
Q

WHEN WILL THE STBY IGNITION TURN ON IF THE SWITCH IS IN NORM?

A

WITH LOSS OF AC POWER

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56
Q

WHEN WILL CONTINUOUS IGNITION COME ON AUTOMATICALLY?

A
  • NAI SELECTED ON
  • FLAPS OUT OF UP
  • N2 BELOW 50%
57
Q

WHAT PROTECTIONS ARE PROVIDED BY THE EEC?

A

OVERSPEED AND OVERBOOST.

58
Q

WHEN IS APPROACH IDLE ACTIVE?

A
  • NAI ON
  • FLAPS IN LANDING POSITION
  • CONTINUOUS IGNITION ON
59
Q

WITH THE APU RUNNING, TURNING OFF THE APU SELECTOR DOES WHAT?

A
  • CLOSES APU BLEED AIR ISOLATION VALVE
  • INITIATES NORMAL SHUTDOWN (60 SECOND COOL DOWN)
  • RESETS AUTO SHUTDOWN FAULT LOGIC EXCEPT WHEN SHUTDOWN DUE TO APU BLEED DUCT LEAK.
60
Q

WHAT ARE THE FIVE THRUST REFERENCES SELECTABLE FROM THE CDU?

A

TO, CLB, CRZ, CON, GA

61
Q

HOW MANY FIRE BOTTLES ARE ON THE BCF?

62
Q

AFTER A FIRE TEST PASS, WHAT TWO SYSTEMS ARE NO LONGER BEING MONITORED BY THE AIRCRAFT?

A
  • WHEEL WELL
  • BLEED DUCT

AOM Vol II, 8-12, fire protection

63
Q

WITH THE ENGINE FUEL SWITCH IN RUN, CAN THE FIRE SWITCH BE PULLED?

A

NOT WITHOUT A FIRE SIGNAL.

64
Q

PULLING THE #1 ENGINE FIRE SWITCH DOES WHAT?

A
  • TRIPS GEN FIELD
  • CLOSES ENG AND SPAR FUEL VALVES
  • CLOSES BLEED AIR VALVE
  • CLOSES HYD SOV (SHUT OFF VALVE)
  • DEPRESSURIZES HYD PUMP
  • ARMS THE SQUIB
65
Q

WITH A MAIN CARGO FIRE, ARMING THE MAIN DECK FIRE SWITCH DOES WHAT?

A
  • ENABLES MAIN DECK FIRE SUPPRESSION
  • TURNS 2 PACKS OFF
  • CONFIGURES EQUIPMENT COOLING TO CLOSED LOOP AND TURNS OFF ALL AIRFLOW TO MAIN DECK AND AIRFLOW AND HEAT INTO LOWER CARGO COMPARTMENTS
  • CLOSES THE MASTER TRIM AIR VALVE.
66
Q

WITH A LOWER FWD CARGO FIRE, PRESSING THE CARGO FIRE DISCHARGE SWITCH DOES WHAT? HOW MANY MINUTES OF PROTECTION IS PROVIDED?

A
  • DISCHARGES 2 BOTTLES THEN AFRTER 30 MIN OR UPON LANDING METER FLOWS OTHER 4 BOTTLES.
  • GIVES 334 MIN OF PROTECTION. (ERF IS 180 MIN)
67
Q

ARE THE ENGINE FIRE LOOPS AN (AND or OR) LOGIC SYSTEM?

A
  • ENGINE ARE “AND” BECAUSE BOTH LOOPS MUST DETECT

- APU IS “OR” BECAUSE EITHER LOOP WILL SET OFF ALARM.

68
Q

WHAT FIRE PROTECTION DO WE HAVE IN THE WHEEL WELL?

69
Q

HOW MANY OVER HEAT LOOPS ARE INSTALLED FOR THE APU?

70
Q

WHERE IS THE APU GROUND CONTROL PANEL LOCATED?

A

RIGHT BODY GEAR WHEEL WELL.

71
Q

THE STABILIZER IS POWERED FROM WHAT HYD SYSTEMS?

72
Q

WHAT IS THE “AUTO” POSITION OF THE STAB TRIM CUTOUT SWITCH FOR?

A

ALLOWS AUTO CUTOUT OF RESPECTIVE SYSTEM IF UNSCHEDULED STAB TRIM IS DETECTED.

73
Q

WHEN ARE THE STAB TRIM SWITCHES ON THE CONTROL WHEEL INHIBITED?

A

MULTIPLE AUTO PILOTS ENGAGED.

74
Q

WHEN DO THE OUTBOARD AILERONS UNLOCK?

75
Q

WITH THE SPEED BRAKE IN ARM, WHEN DO THE SPEED BREAKS DEPLOY ON LANDING? NOT ARMED?

A
  • THRUST LEVERS 1 AND 3 CLOSES
  • MAIN GEAR TOUCH DOWN

WITH SPEED BREAKS NOT ARMED

  • THRUST LEVERS 1 AND 3 CLOSES
  • MAIN GEAR TOUCH DOWN
  • 2 OR 4 REVERSE LEVER PULLED TO REVERSE IDLE.
76
Q

WHAT FLAP PROTECTION IS PROVIDED IN SECONDARY MODE?

A

ASYMMETRY ONLY.

Vol II, flight controls, flap control pg 9-24

77
Q

WHAT WILL OCCUR IF THE TRAILING EDGE FLAP GROUP IS IN THE SECONDARY MODE WITH HYDRAULIC PRESSURE AVAILABLE?

A

REMAIN IN SECONDARY MODE UNTIL FULLY RETRACTED.

78
Q

IN THE ALTERNATE CONTROL MODE, HOW IS FLAP EXTENSION SEQUENCED?

A

ALL LEADING AND TRAILING EDGE FLAP GOUPS BEGING EXTENDING IMMEDIATELY AT THE SAME TIME.

Vol II, flight controls, flap sequencing pg 9-25

79
Q

ON LANDING, WHY DOES THE FLAP POSITION INDICATOR CHANGE FROM GREEN TO MAGENTA?

A

DUE TO INBOARD AND MID-SPAN LE FLAPS RETRACT WHEN REVERSE THRUST IS COMMANDED.

80
Q

WHAT IS THE MAX ALTITUDE FOR FLAP EXTENSION?

81
Q

WHEN IS THE PITCH LIMIT INDICATOR DISPLAYED ON THE PFD AND WHAT IS ITS PURPOSE?

A

FLAPS OUT OF UP AND IS STICK SHAKER ACTIVATION POINT.

82
Q

WHAT IS THE INPUT SOURCE(S) FOR THE COMMAND SPEED DISPLAY ON THE PFD?

A

MCP, FMC AND INPUTS IN TO THE FMS.

83
Q

WHAT IDENTIFIES THE ACTIVE WAY POINT ON THE ND?

A

MAGENTA STAR.

84
Q

THE ALTITUDE RANGE ARC (GREEN ARC) DISPLAYS WHAT INFORMATION?

A

INDICATES WHERE MCP ALTITUDE WILL BE REACHED BASED ON VERTICAL AND GROUND SPEED.

85
Q

THE WXR, STA, WPT, ARPT, DATA, POS, TERR SWITCHES ON THE EFIS CONTROL PANEL DISPLAY WHAT INFORMATION WHEN PUSHED (EACH INDIVIDUALLY?

A
  • WXR - POWERS RADAR TRANSCEIVERS SELECTED ON WX RADAR CONTROL PANEL
  • STA - DISPLAYS HIGH AND LOW VOR’S WHEN ND RANGE IS IN 40nm OR LESS AND DISPLAYS HIGH VOR’S WHEN ND RANGE IS 80, 160, 320 OR 640nm
  • WPT - IN MAP AND MAP CTR MODES DISPLAYS WAYPOINTS WHEN ND RANGER SELECTOR IS 40nm OR LESS
  • ARPT - IN MAP AND MAP CTR MODES DISPLAYS AIRPORTS IN ALL RANGES THAT HAVE RUNWAYS 7500ft OR LONGER
  • DATA - IN PLAN, MAP AND MAP CTR MODES DISPLAYS FMC ETA ALTITUDE AT EACH WAYPOINT AND ALTITUDE CONSTRAINTS AT EACH WAYPOINT.
  • POS - IN MAP AND MAP CTR MODES DISPLAYS VOR RAW DATA, RADIAL EXTENDED FROM NOSE OF AIRPLANE TO THE VOR STATIONS DISPLAYED ON CDU NAV RAD PAGE. WHEN COLLOCATED DEME DATE RECEIVED TICK MARK DISPLAYED AT DME DISTANCE. RADIAL EXTEND TO EDGE OF DISPLAY IN NO VALID DME DATA RECEIVED, DISPLAYS IRU’S AND GPS POSITIONS.
  • TERR - DISPLAYS TERRAIN INFORMATION ON ND
86
Q

IF THE CAPTAIN’S INBD AND LWR (EICAS) CRT IS INOPERATIVE, HOW AND WHERE COULD THE HYD SYNOPTIC INFORMATION BE DISPLAYED?

A

ON FO’S ND BY SELECTING EICAS ON INBD CRT KNOB.

87
Q

IN WHAT ND MODE WILL WEATHER RADAR NOT BE DISPLAYED?

A

PLAN, VOR CTR, APPR CTR

88
Q

WHAT INDICATES A ROUTE MODIFICATION ON THE ND?

A

A WHITE DASHED LINE.

89
Q

THE STANBY HORIZON IS POWERED FROM WHAT SOURCE?

A

MAIN BATTERY BUS.

90
Q

WHEN WILL THE G/S AND LOC INDICATOR/SCALES DISPLAY AND WHEN WILL THEY FILL SOLID MAGENTA?

A

BOTH INDICATORS DISPLAY WHEN TUNED AND SIGNAL IS RECEIVED, THEY FILL IN SOLID WHEN WITH IN 2 1/3 DOTS FORM THE CENTER.

Vol II, flight instruments, pg 10-9

91
Q

WHAT IS THE MAXIMUM AMOUNT FO FUEL WE CAN CARRY IN POUNDS WITH A FUEL DENSITY OF 6.7 lbs PER GALLON?

A

359,414 lbs

92
Q

WITH THE A/C COMPLETELY FULL OF FUEL, DISCUSS THE DIFFERENT FUEL CONFIGURATIONS BEGINNING WITH ENGINE START THROUGH LANDING?

A
  • ALL BOOST PUMP SWITCHES ARE ON. CWT FEED ALL ENGINES
  • WHEN FLAPS REACH 10° CROSSFEED VALVES 2 and 3 CLOSE
  • OVERRIDE JETT PUMPS 2 and 3 ARE ARMED
  • CWT PUMPS ARE PROVIDING FUEL TO ENGINES 1 and 4 AND MAIN TANK PUMPS ARE PROVIDING FUEL TO ENGINES 2 and 3 RESPECTIVELY
  • AFTER TAKEOFF WHEN THE FLAPS ARE UP, CROSSFEED VALVES 2 and 3 ARE COMMANDED OPEN
  • THE CWT PUMPS PROVIDE FUEL TO ALL ENGINES
  • IN CLIMB IF “FUEL LOW CTR L/R” MESSAGE IS DISPLAYED, TANK QUANTITY IS APPROX 7000lbs, CWT PUMPS SELECTED OFF
  • IN CRUISE WHEN “FUEL OVD CTR L/R” IS DISPLAYED AND TANK QUANTITY IS 4000lbs OR MORE, CWT PUMPS SHOULD BE SELECTED BACK TO ON
  • WITH APPROX 40,200lbs IN MAIN TANKS 2 and 3, THE RESERVE TANK TRANSFER VALVES OPEN AND FUEL GRAVITY TRANSFERS TO MAIN TANKS 2 and 3
  • WHEN “FUEL LOW CTR” IS DISPLAYED AND CWT IS LESS THAN 3000lbs PUMPS SHOULD BE SELECTED OFF. FUEL SCAVENGE PUMP ACTIVATES IN THE CWT AND SCAVENGES FUEL TO MAIN TANK 2
  • OVERRIDE/JETT PUMPS 2 and 3 ACTIVATE WHEN CWT PUMPS ARE SELECTED OFF. OVERRIDE/JETT PUMP 2 PROVIDE FUEL TO ENGINES 1 and 2 AND OVERRIDE/JETT PUMP 3 PROVIDES FUEL TO ENGINES 3 and 4
  • WHEN ALL TANKS ARE EQUAL IN QUANTITY (APPROX 29,000lbs) “FUEL TANK/ENG” IS DISPLAYED. OVERRIDE/JETT PUMPS SHOULD BE SELECTED TO OFF AND CROSSFEED VALVES 1 and 4 CLOSED. ALL MAIN PUMPS ARE NOW FEEDING RESPECTIVE ENGINES.
93
Q

HOW DO WE, AND WHAT HAPPENS WHEN WE JETTISON FUEL?

A
  • Jettison is initiated by rotating jettison selector knob to A or B. When A or B is selected fuel temp is replaced by “To Remain”
  • If a failure occurs in one channel you must select other channel
  • Jettison time to dump is displayed on fuel synop
  • Allow 90 seconds for system to calculate dump time
  • Rotating fuel to remain knob decreases or increases quantity
  • Pushing either jettison nozzle valve switch on activates all ovrd/jett pumps in the tanks containing fuel (Pump switches must be on)
  • Jettison control system controls fuel balancing between tanks 2&3
  • If balancing is required ovrd/jett pumps in low tank deactivate until tanks are balanced
  • Reserve transfer valves open when main tanks 2 or 3 qty is decreased to 40,000lbs Fuel transfers from reserve tanks 2&3 to respective main tanks
  • When either main tank 2 or 3 qty decreases to 20,000lbs during jettison both main tank 1&4 transfer valves open Jettison terminates when fuel to remain has been reached Fuel to remain qty changes color
    from magenta to white and flashes for 5 seconds, Jettison control system deactivates all operating pumps.
94
Q

WHAT IS THE DIFFERENCE BETWEEN TOTAL FUEL AND CALCULATED FUEL? WHEN ARE THE VALUES DIFFERENT?

A
  • TOTAL FUEL IS THE FUEL ONBOARD AS INDICATED BY THE FUEL QTY SYSTEM
  • CALCULATED FUEL, PRIOR TO ENGINE START, DISPLAYS FUEL QUANTITY CALCULATED BY THE FUEL QUANTITY PROCESSOR. AFTER ENGINE START, IT DISPLAYS FUEL QUANTITY CALCULATED BY DECREASING FUEL ON BOARD AT ENGNE START AT EICAS FUEL FLOW SIGNAL RATE
  • THEY ARE DIFFERENT WITH A FUEL LEAK.
95
Q

PRIOR TO ENGINE START, WITH USABLE FUEL IN THE CWT, AFTER FUEL PUMP CONFIGURATIOn, ARE THE 2 & 3 OVERRIDE/JETTISON PUMPS “ON or ARMED”?

96
Q

WHAT IS THE PURPOSE OF THE # 1 and 4 TRANSFER VALVES?

A
  • VALVE OPENS AND GRAVITY TRANSFERS FROM OUTBOARD TO INBOARD MAIN TANK TO APPROX 7000lbs REMAINING IN EACH OUTBOARD MAIN TANK
  • DURING JETTISON, VALVES OPEN WHEN EITHER MAIN TANK 2 & 3 FUEL DECREASES TO 20,000lbs
  • VALVES MAY BE OPENED MANUALLY USING THE FUEL TRANSFER MAIN 1 & 4 SWITCH ON OVERRIDE PANEL.
97
Q

DOES THE FLOW BAR DISAPPEAR IN THE CROSS FEED # 2 and 3 VALVE SWITCHES WHEN THE FLAPS ARE SELECTED TO THE TAKEOFF POSITION?

98
Q

AFTER POSITIONING THE FUEL JETTISON SELECTOR TO A or B, WHERE DOES THE FUEL JETTISON VALUE DISPLAY?

A

REPLACES FUEL TEMP ON PRIMARY EICAS.

99
Q

ONCE ACTIVATED, HOW LONG WILL THE SCAVENGE PUMP OPERATE?

A

120 MIN OR UNTIL CTR TANK LOW PRESSURE IS SENSED.

100
Q

WHAT THREE THINGS WILL ILLUMINATE THE HYD SYSTEM FALULT LIGHT?

A

LOW SYSTEM PRESSURE AND QUANTITY.

101
Q

WHAT WILL TRUN ON THE #4 DEMAND PUMP IF THE SWITCH IS IN AUTO?

A
  • FUEL CONTROL SWITCH SELECTED OFF
  • LOW EDP PRESSURE
  • FLAPS IN TRANSIT ON GROUND OR OUT OF UP IN FLIGHT (1 AND 4 ONLY)
102
Q

ON DECENT IN KLAX, THE #4 HYDRAULIC QUANTITY GOES TO ZERO. WHAT SYSTEMS WILL BE AFFECTED FOR THE APPROACH AND LANDING?

A
  • OUTBOARD TE FLAPS
  • NORMAL BRAKES
  • WING GEAR ACTUATION
  • SPOILERS 5, 6, 7 AND 8
  • RIGHT OUTBOARD ELEVATOR AND AUTOBRAKES
103
Q

WITH THE LOSS OF #1 HYD QUANTITY, WHAT SYSTEMS WILL BE AFFECTED FOR THE APPROACH AND LANDING?

A
  • INBOARD TE FLAPS
  • NOSE/BODY GEAR ACTUATION
  • NOSE BODY GEAR STEERING
  • CENTER AUTOPILOT
  • ALTERNATE BRAKE SOURCE
  • LEFT OUTBOARD ELEVATOR
104
Q

WITH LOSS OF HYD SYSTEM 2 AND 3, WHY IS THERE A SPEED ADDITIVE FOR THE APPROACH?

A
  • STAB TRIM LOSS

- LOSS OF ELEVATOR FEEL

105
Q

ON LANDING, THE BRAKE SOURCE LIGHT ILLUMINATES, WHAT DOES THIS MEAN>

A

LOSS OF NORMAL AND ALTERNATE BRAKES (HYD SYSTEMS 4, 1 AND 2)

106
Q

THE DEMAND PUMPS ARE POWERED HOW?

A
  • 1 AND 4 PNEUMATIC
  • 2 AND 3 ELECTRIC
    (note: PW all are pneumatic)
107
Q

THE AUX PUMP(S) IS POWERED FROM WHICH SOURCE?

A

GROUND HANDLING BUS.

108
Q

WITH THE #4 AUX PUMP ON AND PROVIDING PRESSURE, WITH HYD SYS FAULT LIGHT BE OFF OR ON?

109
Q

WHAT IS THE MINIMUM HYDRAULIC QUANTITY FOR DISPATCH? WHERE DO YOU READ THAT VALUE?

A
  • 0.80

- HYD STAT PAGE

110
Q

HOW MANY TIRES DO WE HAVE AND WHAT IS THEIR NUMERICAL ORDER?

111
Q

SELECTING VALUE 3 ON THE AUTO BRAKE SELECTOR DOES WHAT? FROM WHCI SOURCE DOES THE AUTO BRAKE SYSTEM RECEIVE DECELERATION INPUTS?

A
  • MAINTAINS THE SELECTED AIRPLANE DECELERATION RATE
  • AUTOBRAKE PRESSURE IS REDUCED AS OTHER CONTROLS, SUCH AS THRUST REVERSERS AND SPOILERS, CONTRIBUTE TO TOTAL DECELERATION. THE SYSTEM PROVIDES BRAKING TO A COMPLETE STOP OR UNTIL IT IS DISARMED.
112
Q

WHAT DOES THE EICAS MESSAGE “GEAR TILT” MEAN?

A

MAIN GEAR TRUCK NOT IN FULL TILT POSITION.

113
Q

HOW DO WE ALTERNATELY EXTEND THE GEAR? WHERE ARE THE SWITCHES LOCATED?

A

SELECTION OF ALTERNATE NOSE/BODY AND WING GEAR SWITCHES LOCATED ON THE LANDING GEAR PANEL.

114
Q

YOU HAVE A WHELL WELL FIRE, WHAT SPEED SHOULD YOU BE AT BEFORE EXTENDING THE GEAR?

A

270 kts/M 0.82

115
Q

ON TAKEOFF ROLL, WHEN DOES “RTO” ARM? WHAT KIND OF BRAKING IS PROVIDED?

A

85 kts

MAX BREAKING

116
Q

WHAT DOES A WHITE HASHED BOX DISPLAYED ON THE (EXPANDED) GEAR POSITION INDICATOR INDICATE?

A

GEAR IS IN TRANSIT

117
Q

HOW LONG DOES THE GEAR UP INDICATION REMAIN IN THE EICAS?

A

10 SECONDS

118
Q

AT WHAT SPEED DOES THE BODY GEAR STEERING DISARM?

119
Q

WHAT DOES THE BREKE TORQUE LIMITING SYSTEM DO?

A

THE SENSORS DETECT EXCESSIVE TORQUE DURING BRAKING TO PREVENT DAMAGE TO LANDING GEAR.
WHEN EXCESSIVE TORQUE IS DETECTED, A SIGNAL IS SENT TO THE ANTI-SKID VALVE TO RELEASE BRAKE PRESSURE TO THAT WHEEL.

120
Q

WHAT ARE THE 3 LEVELS OF EICAS ALERTING?

A

WARNING
CAUTION
ADVISORY

121
Q

CAN A WARNING EICAS MESSAGE BE CANCELED?

122
Q

WHEN ARE THE FIRE BELL AND MASTER WARNING LIGHTS INHIBITED?

A

V1 TILL 400FT RA OR 25 SEC AFTER V1

123
Q

WHAT ITEMS WILL ACTIVATE THE TAKEOFF CONFIGURATION WARNING?

A
  • N1 AT 70%
  • PARKING BREAK SET
  • BODY GEAR NOT CENTERED
  • STAB TRIM NOT IN GREEN BAND
  • FLAPS NOT IN TAKE OFF POSITION
  • SPEEDBRAKE NOT STOWED
    now also wrong runway in FMS
124
Q

WHEN IS THE WINDSHEAR ALERT SYSTEM ACTIVE?

A

Vr to 1500FT

125
Q

IN WHAT PHASE OF FLIGHT WILL YOU GET A “GPWS” SINK RATE WARNING?

A

IF YOU HAVE AN EXCESSIVE DESCENT RATE AT ANY TIME.

126
Q

WHAT IS THE PURPOSE OF THE EVENT RECORD SWITCH? HOW MANY EVENTS CAN BE RECORDED?

A

PUSHING THE EICAS EVEN RCD SWITCH RECORDS CURRENTLY DISPLAYED ENGINE INDICATIONS AND ADDITIONAL EICAS MAINTENANCE INFORMATION.
UP TO 5 EVENTS CAN BE RECORDED, IT ALSO RECORDS OUT OF LIMIT PARAMETERS.

127
Q

WHAT IS A STATUS MESSAGE?

A

INDICATES EQUIPMENT FAULTS REQUIRING “MEL” REFERENCES FOR DISPATCH.

128
Q

WHAT DOES THE “TCAS” ALERT “TRAFFIC, TRAFFIC” MEAN?

A

A “TA” IS A PREDICTION ANOTHER AIRCRAFT WILL ENTER THE CONFLICT AIRSPACE IN 25-45 SECONDS.

129
Q

WHAT SWITCH TURNS ON TCAS ADVISORIES ON ND?

A

“TFC” BUTTON ON THE EFIS CONTROL PANEL.

130
Q

WHAT IS THE ALLOWED WIND SPEED WHEN OPERATING THE MAIN CARGO DOOR?

A

DOOR OPERATING 40kts
DOOR OPENED 65kts

Vol I, General Limitations

131
Q

WHAT IS THE MAX ZFW ON THE BCF’S?

A

610,000 lbs

132
Q

WHAT IS THE MAX TAILWIND FOR TAKEOFF AND LANDING?

133
Q

MAX TAKEOFF CROSSWIND COMPONENT FOR A DRY RUNWAY? LANDING?

A

40kts TAKEOFF
36kts LANDING

Vol I, General Limitations

134
Q

MAX DEPTH OF SLUSH FOR LANDING?

A

0.5”

Vol I, General Limitations

135
Q

WHAT IS THE MAX LANDING WEIGHT OF THE ERF?

A

653,000lbs

136
Q

WHAT IS THE MINIMUM CREW OXYGEN DISPATCH PRESSURE?

137
Q

WHAT IS THE MINIMUM “TCH”?

138
Q

MAX N1?

139
Q

MAX ENGINE START EGT?

A

750º GE ENGINES

747 SKV KALITTA (1 decks)

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