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B777 FCOM > QRH Checklists > Flashcards

QRH Checklists Flashcards

1
Q
  1. Miscellaneous

BOMB WARNING IN FLIGHT

A

A bomb warning is received in flight

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2
Q
  1. Miscellaneous

BOMB WARNING ON GROUND

A

A bomb warning is received while on the ground

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3
Q
  1. Miscellaneous

DITCHING

A

Airplane ditching and evacuation are needed

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4
Q
  1. Miscellaneous

HIJACK

A

A hijack is in progress

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5
Q
  1. Miscellaneous

OVERWEIGHT LANDING

A

A landing at greater than maximum landing weight is needed

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6
Q
  1. Airplane General

Automatic Unlock

A

The correct emergency code access is entered.

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7
Q
  1. Airplane General

CREW OXYGEN LOW

A

Crew oxygen pressure is low

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8
Q
  1. Airplane General

[] DOOR AFT CARGO

VPD-VPF

A

VPD-VPF

The aft lower cargo door is not closed and secured.

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9
Q
  1. Airplane General

[] DOOR AFT CARGO

VOZ, VPH

A

VOZ, VPH

The aft lower cargo door is not closed and secure

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10
Q
  1. Airplane General

[] DOOR BULK CARGO

A
  1. [] DOOR BULK CARGO

The bulk cargo door is not closed and secure

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11
Q
  1. Airplane General

[] DOOR E/E ACCESS

A
  1. [] DOOR E/E ACCESS

The electrical and electronic access door is not closed and secure

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12
Q
  1. Airplane General

[] DOOR ENTRY 1-5L, R

A
  1. [] DOOR ENTRY 1-5L, R

An entry door is not closed and secure

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13
Q
  1. Airplane General

[] DOOR FWD ACCESS

A
  1. [] DOOR FWD ACCESS

The forward access door is not closed and secure

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14
Q
  1. Airplane General

[] DOOR FWD CARGO

A
  1. [] DOOR FWD CARGO

The forward lower cargo door is not closed and secure

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15
Q
  1. Airplane General

DOOR WING SLIDE L, R

A
  1. DOOR WING SLIDE L, R

The door for the unpressurised wing slide compartment is not secure

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16
Q
  1. Airplane General

DOORS

A
  1. DOORS

Two or more doors are not closed and secure

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17
Q
  1. Airplane General

ELT ON

A
  1. ELT ON

The emergency locator transmitter is on

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18
Q
  1. Airplane General

EMER LIGHTS

A
  1. EMER LIGHTS

One of these occurs:
• The emergency lights are on;
• The emergency lights switch is not ARMED

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19
Q
  1. Airplane General

LOCK FAIL

A
  1. LOCK FAIL

One or more of these occur:
• The flight deck access system switch is off;
• The lock is failed.

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20
Q
  1. Airplane General

PASS OXYGEN LOW

A
  1. PASS OXYGEN LOW

The Passenger oxygen pressure is low

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21
Q
  1. Airplane General

PASS OXYGEN ON

A
  1. PASS OXYGEN ON

The passenger oxygen system is on

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22
Q
  1. Airplane General

WINDOW DAMAGE FWD L, R

A
  1. WINDOW DAMAGE FWD L, R
The forward flight deck window has one or more of these:
• An electrical arc;
• A delamination;
• A crack;
• Is shattered.
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23
Q
  1. Airplane General

WINDOW DAMAGE SIDE L, R

A
  1. WINDOW DAMAGE SIDE L, R
The side flight deck window has one or more of these:
• An electrical arc;
• A delamination;
• A crack;
• Is shattered.
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24
Q
  1. Airplane General

[] WINDOW FLT DECK L, R

A
  1. [] WINDOW FLT DECK L, R

The side window is not closed and secure

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25
Q
  1. Airplane General

[] WINDOWS

A
  1. [] WINDOWS

The left and right side windows are not closed and secure

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26
Q
  1. Air Systems

[] CABIN ALTITUDE (M)

A
  1. [] CABIN ALTITUDE (M)
Cabin Altitude is excessive (M)
1 don oxy masks
2 establish crew communications
3 check cabin altitude and rate
4 if cabin alt uncontrollable:
   - pax oxygen switch.. push on and hold 1 second
   - descend LSA or 10000 if higher
      • thrust to idle
      • extend speedbrakes
      • if struct integ in doubt
         - limit airspeed 
         - avoid high manoeuvring loads
      • descend at Vmo/Mmo
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27
Q
  1. Air Systems

BLEED ISLN CLOSED C, L, R

A
  1. BLEED ISLN CLOSED C, L, R

One of the following occurs:
• the isolation valve has failed closed;
• the bleed isolation switch is off

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28
Q
  1. Air Systems

BLEED ISLN OPEN C, L, R

A
  1. BLEED ISLN OPEN C, L, R

The isolation valve is failed open

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29
Q
  1. Air Systems

[] BLEED LEAK BODY

A
  1. [] BLEED LEAK BODY

A bleed air leak occurs in the body area

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30
Q
  1. Air Systems

[] BLEED LEAK L, R

A
  1. [] BLEED LEAK L, R

A bleed air leak occurs in the wing or pack bay area

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31
Q
  1. Air Systems

[] BLEED LEAK STRUT L, R

A
  1. [] BLEED LEAK STRUT L, R

A bleed air leak or starter duct leak occurs in the strut area.

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32
Q
  1. Air Systems

[] BLEED LOSS BODY

A
  1. [] BLEED LOSS BODY

Bleed air from the left and right body ducts is not available.

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33
Q
  1. Air Systems

[] BLEED LOSS BODY L

A
  1. [] BLEED LOSS BODY L

Bleed air from the left body duct is not available.

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34
Q
  1. Air Systems

[] BLEED LOSS BODY R

A
  1. [] BLEED LOSS BODY R

Bleed air from the right body duct is not available

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35
Q
  1. Air Systems

[] BLEED LOSS WING L, R

A
  1. [] BLEED LOSS WING L, R

Bleed air from the wing duct is not available

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36
Q
  1. Air Systems

BLEED OFF APU

A
  1. BLEED OFF APU

One of the following occurs:
• The APU bleed valve is closed because of a system fault;
• The APU bleed switch is off.

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37
Q
  1. Air Systems

BLEED OFF ENG L, R

A
  1. BLEED OFF ENG L, R

One of the following occurs:
• The engine bleed valve is closed because of a system fault;
• The engine bleed switch is off.

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38
Q
  1. Air Systems

[] CABIN ALTITUDE AUTO

A
  1. [] CABIN ALTITUDE AUTO

One of these occurs:
• Automatic pressurisation control is failed;
• Both outflow valve switches are in manual.

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39
Q
  1. Air Systems

CARGO HEAT AFT

A
  1. CARGO HEAT AFT

One of these occurs:
• Aft lower cargo heat is inoperative;
• The aft cargo temperature selector is OFF.

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40
Q
  1. Air Systems

CARGO HEAT BULK

A
  1. CARGO HEAT BULK

One of these occurs:
• bulk cargo heat is inoperative;
• the bulk cargo temperature selector is off.

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41
Q
  1. Air Systems

EQUIP COOLING

A
  1. EQUIP COOLING

The forward equipment cooling system is failed

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42
Q
  1. Air Systems

[] EQUIP COOLING OVRD

A
  1. [] EQUIP COOLING OVRD

The equipment cooling system is in override mode.

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43
Q
  1. Air Systems

[] LANDING ALTITUDE

A
  1. [] LANDING ALTITUDE

One of these occurs:
• The FMC does not supply a landing altitude;
• The landing altitude selector is pulled.

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44
Q
  1. Air Systems

[] OUTFLOW VALVE AFT, FWD

A

One of these occurs:
• Automatic control of the outflow valve is inoperative;
• The outflow valve switch is in manual.

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45
Q
  1. Air Systems

[] PACK L

A

The left pack is inoperative

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46
Q
  1. Air Systems

[] PACK L+R

A

Both packs are inoperative

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47
Q
  1. Air Systems

[] PACK MODE L, R

A

The pack is in the standby mode.

Note: At lower altitudes or higher outside air temperatures, the pack may shut down.

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48
Q
  1. Air Systems

[] PACK R

A

The right pack is inoperative

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49
Q
  1. Air Systems

[] TRIM AIR L, R

A

The trim air valve is closed

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50
Q
  1. Anti-Ice, Rain

[] ANTI-ICE ENG L, R

A

The engine anti-ice valve is closed when commanded open

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51
Q
  1. Anti-Ice, Rain

[] ANTI-ICE LEAK ENG L, R

A

A bleed air leak occurs in the engine anti-ice duct

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52
Q
  1. Anti-Ice, Rain

ANTI-ICE LOSS ENG L, R

A

Anti-ice bleed air for the engine is not available

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53
Q
  1. Anti-Ice, Rain

[] ANTI-ICE ON

A

All of these occur:
• wAn anti-ice selector is ON;
• TAT is more than 10 degrees C;
• Ice is not detected.

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54
Q
  1. Anti-Ice, Rain

[] ANTI-ICE WING

A

One or both wing anti-ice valves are failed closed.

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55
Q
  1. Anti-Ice, Rain

[] HEAT PITOT C

A

The Center pitot probe heat is failed.

Note: The standby air data is unreliable in icing conditions.

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56
Q
  1. Anti-Ice, Rain

[] HEAT PITOT L

A

The left pitot probe heat is failed.

Note: The PFD air data is not affected by single pitot heat failure. Ensure that the right AIR DATA/ATT source switch stays off.

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57
Q
  1. Anti-Ice, Rain

[] HEAT PITOT L+C+R

A

The left, Center and right pitot probe heat are failed.

Note: The air data is unreliable in icing conditions.

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58
Q
  1. Anti-Ice, Rain

[] HEAT PITOT R

A

The right pitot probe heat is failed.

Note: The PFD air data is not affected by single pitot heat failure. Ensure that the left AIR DATA/ATT source switch stays off.

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59
Q
  1. Anti-Ice, Rain

ICE CRYSTAL ICING

A

Engine ice crystal icing or TAT probe icing is suspected. Ice crystal icing conditions exist when in visible moisture, and one or more of the following indications are present:
• Amber or red weather radar returns below the aeroplane;
• Appearance of liquid water on the windshield temperatures too low for rain (the sound is different than rain);
• The autothrottle disconnects or is unable to maintain the selected airspeed;
• TAT indication on EICAS stays near 0° C;
• Abnormal engine vibration indications.

(additional items that can indicate ice crystal icing are listed in the additional information section)

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60
Q
  1. Anti-Ice, Rain

[] ICE DETECTORS

A

The ice detectors are failed.

Note: Run the engine and wing anti-icing systems manually.

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61
Q
  1. Anti-Ice, Rain

ICING ENG

A

Ice is detected and an engine anti-ice selector is off.

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62
Q
  1. Anti-Ice, Rain

ICING WING

A

Icing is detected and one of these occurs:
• The wing anti-ice selector is OFF;
• The wing anti-ice takeoff inhibit is active.

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63
Q
  1. Anti-Ice, Rain

[] WINDOW HEAT L, R FWD

A

Primary window heat for the forward window is inoperative.

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64
Q
  1. Anti-Ice, Rain

[] WINDOW HEAT L, R SIDE

A

Window heat for the side window is inoperative

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65
Q
  1. Automatic Flight

AUTOPILOT

A

One or more of these occur:
• The autopilot is in a degraded mode other than the selected mode;
• The engaged roll mode is failed;
• The engaged pitch mode is failed;
• The autopilot is in flight envelope protection.

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66
Q
  1. Automatic Flight

AUTOPILOT DISC

A

All autopilots are disengaged

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67
Q
  1. Automatic Flight

AUTOTHROTTLE DISC

A

Both autothrottles are disconnected

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68
Q
  1. Automatic Flight

[] AUTOTHROTTLE L, R

A

The Autothrottle is inoperative

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69
Q
  1. Automatic Flight

NO AUTOLAND

A

The autoland system is not available

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70
Q
  1. Automatic Flight

NO LAND 3

A

The autoland system does not have redundancy for a triple channel autoland

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71
Q
  1. Communications

DATALINK LOST

A

The ACARS datalink is temporarily lost

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72
Q
  1. Communications

DATALINK SYS

A

The datalink system is failed

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73
Q
  1. Communications

[] RADIO TRANSMIT

A

The microphone switch is on and causes a radio to transmit for 40 seconds or more.

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74
Q
  1. Communications

SATCOM

A

The SATCOM system is failed

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75
Q
  1. Communications

SATCOM DATALINK

A

The SATCOM datalink is failed

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76
Q
  1. Communications

SATCOM VOICE

A

SATCOM voice communication is failed

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77
Q
  1. Communications

SATVOICE LOST

A

SATCOM voice communication is temporarily lost

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78
Q
  1. Communications

VHF DATALINK

A

The VHF datalink is failed

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79
Q
  1. Electrical

[] ELEC AC BUS L, R

A

The AC Bus is not energised

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80
Q
  1. Electrical

[] ELEC BACKUP GEN L, R

A

The backup generator is failed

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81
Q
  1. Electrical

[] ELEC BACKUP SYS

A

The backup power system is failed

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82
Q
  1. Electrical

ELEC BATTERY OFF

A

The battery switch is off

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83
Q
  1. Electrical

ELEC BUS ISLN L, R

A

The bus tie breaker is open

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84
Q
  1. Electrical

ELEC CABIN/UTIL OFF

A

The cabin/utility power switch is OFF

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85
Q
  1. Electrical

[] ELEC GEN DRIVE L, R

A

A generator drive fault occurs

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86
Q
  1. Electrical

[] ELEC GEN OFF APU

A

The generator control breaker is open

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87
Q
  1. Electrical

[] ELEC GEN OFF L, R

A

The generator control breaker is open

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88
Q
  1. Electrical

ELEC GRD HDLG BUS

A

A fault occurs in the ground handling bus

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89
Q
  1. Electrical

ELEC IFE/SEATS OFF

A

The IFE/passenger seats power switch is OFF.

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90
Q
  1. Electrical

ELEC STANDBY SYS

A

A standby power system failure occurs

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91
Q
  1. Electrical

[] MAIN BATTERY DISCH

A

One of these occurs:
• The main battery is discharging;
• The hot battery bus is not energised.

Note: The main battery can power the standby system for a minimum of 10 minutes.

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92
Q
  1. Engines, APU

ABORTED ENGINE START L, R (M)

A

On the ground, an aborted engine start is needed
(M)
1. FUEL CONTROL switch (effected side)… CUTOFF

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93
Q
  1. Engines, APU

DUAL ENG FAIL/STALL (M)

A

Engine speed for both engines is below idle
(M)
1. FUEL CONTROL switches (both)… CUTOFF, then RUN;
2. RAM AIR TURBINE switch… Push and hold for 1 second

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94
Q
  1. Engines, APU

[] ENG AUTOSTART L, R (M)

A

During ground start, one of these occurs:
• Autostart did not start the engine;
• Fuel control switch is in RUN at low engine RPM with the auto start switch OFF.
(M)
1. FUEL CONTROL switch (affected side)… CUTOFF.

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95
Q
  1. Engines, APU

ENG LIM/SURGE/STALL L, R (M)

A

One or more of these occur:
• Engine indications are abnormal;
• Engine indications are quickly nearing or showing an exceedance;
• Abnormal engine noises are heard, possibly with airframe vibration;
• There is no response to thrust lever movement or the response is abnormal;
• Flames in the engine inlet or exhaust are reported.
(M)
1. A/T ARM switch (affected side)… Confirm… OFF;
2. Thrust Lever (affected side)… Confirm… Retard until engine indications stay within limits or the thrust lever is at idle.

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96
Q
  1. Engines, APU

ENG SVR DAMAGE/SEP L, R (M)

A

One or more of these occur:
• Airframe vibrations with abnormal engine indications;
• Engine separation.
(M)
1. A/T ARM switch (affected side)… Confirm… OFF;
2. Thrust Lever (affected side)… Confirm… Idle;
3. FUEL CONTROL Switch (affected side)… Confirm… CUTOFF;
4. Engine Fire Switch (affected side)… Confirm… Pull.

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97
Q
  1. Engines, APU

[] APU LIMIT

A

An APU limit exceedance occurs.

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98
Q
  1. Engines, APU

[] APU SHUTDOWN

A

An APU automatic shutdown occurs.

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99
Q
  1. Engines, APU

ENG AUTOSTART OFF

A

The engine autostart switch is off

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100
Q
  1. Engines, APU

ENG CONTROL L, R

A

An EEC system fault occurs.

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101
Q
  1. Engines, APU

[] ENG EEC MODE L, R

A

The EEC is in the alternate control mode

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102
Q
  1. Engines, APU

[] ENG FAIL L, R

A

Engine speed is below idle

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103
Q
  1. Engines, APU

[] ENG FUEL FILTER L, R

A

Fuel contamination can cause fuel to bypass the engine fuel filter.

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104
Q
  1. Engines, APU

[] ENG FUEL VALVE L, R

A

One or more of these occur:
• The engine fuel valve is not in the commanded position;
• The fuel spa valve is not in the commanded position.

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105
Q
  1. Engines, APU

ENG IDLE DISAGREE

A

One engine is at approach idle and the other is at minimum idle

106
Q
  1. Engines, APU

ENG IN-FLIGHT START L, R

A

And engine start is needed and all of the following are true:
• There is N1 rotation;
• There was NO engine fire;
• There is NO abnormal airframe vibration.

107
Q
  1. Engines, APU

[] ENG LIMIT PROT L, R

A

The EEC is in the alternate mode and the commanded N1 exceeds the limit.

108
Q
  1. Engines, APU

[] ENG OIL FILTER L, R

A

Oil filter contamination has caused oil to bypass the oil filter

109
Q
  1. Engines, APU

[] ENG OIL PRESS L, R

A

The engine oil pressure is low

110
Q

[] ENG OIL TEMP L,R

A

The engine oil temperature is high

111
Q
  1. Engines, APU

[] ENG REV LIMITED L, R

A

The engine Reverser operation is limited.

Note: On landing, the effected thrust reverser will not deploy or affected reverse thrust will be limited to idle.

112
Q
  1. Engines, APU

ENG REVERSER L, R

A

A fault occurs in the thrust reverser system

113
Q
  1. Engines, APU

ENG RPM LIMITED L, R

A

Engine thrust is at the N1 or N2 red line limit.

114
Q
  1. Engines, APU

ENG SHUTDOWN

A

Both engines were shut down by the fuel control switches or the engine fire switches

115
Q
  1. Engines, APU

ENG SHUTDOWN L, R

A

The engine was shutdown by the fuel control switch or the engine fire switch.

116
Q
  1. Engines, APU

[] ENG START VALVE L, R

A

The start valve is not in the commanded position.

117
Q
  1. Engines, APU

[] ENG STARTER CUTOUT L, R

A

One of these occurs:
• The start valve fails to close;
• The start selector stays in start.

118
Q
  1. Engines, APU

ENG THRUST L, R

A

The engine thrust is less than the commanded thrust

119
Q
  1. Engines, APU

VOLCANIC ASH

A

Volcanic ash is suspected when one or more of these occur:
• A static discharge around the windshield;
• A bright glow in the engine inlets;
• Smoke or dust in the flightdeck;
• An acrid odour.

120
Q
  1. Fire Protection

[] FIRE APU

A

Fire is detected in the APU

121
Q
  1. Fire Protection

[] FIRE ENG L, R (M)

A

Fire is detected in the engine.
(M)
1. A/T ARM switch (affected side)… Confirm… OFF;
2. Thrust Lever (affected side)… Confirm… Idle;
3. FUEL CONTROL switch (affected side)… Confirm… CUTOFF;
4. Engine fire switch (affected side)… Confirm… Pull;
5. If the FIRE ENG message stays shown:
• Engine fire switch (affected side)… Rotate to the stop and hold for 1 second;
• If after 30 seconds, the FIRE ENG message stays shown:
- Engine fire switch (affected side)… Rotate to the other stop and hold for 1 second.

122
Q
  1. Fire Protection

FIRE ENG TAILPIPE L, R

A

An engine tailpipe fire occurs on the ground with no fire warning.

123
Q
  1. Fire Protection

SMOKE, FIRE OR FUMES

A

Smoke, fire or fumes occurs

124
Q
  1. Fire Protection

BOTTLE 1, 2 DISCH ENG

A

The engine fire extinguisher bottle pressure is low

125
Q
  1. Fire Protection

BOTTLE DISCH APU

A

The APU fire bottle pressure is low.

126
Q
  1. Fire Protection

BOTTLE DISCH CARGO

A

Both rapid discharge cargo fire extinguisher bottle pressures are low

127
Q
  1. Fire Protection

[] DET FIRE APU

A

APU fire detection is failed

128
Q
  1. Fire Protection

DET FIRE CARGO AFT, FWD

A

Lower cargo compartment smoke detection is failed

129
Q
  1. Fire Protection

DET FIRE ENG L, R

A

Engine fire and overheat detection is failed

130
Q
  1. Fire Protection

[] FIRE CARGO AFT

A

Smoke is detected in the aft lower cargo compartment.

131
Q
  1. Fire Protection

[] FIRE CARGO FWD

A

Smoke is detected in the forward lower cargo compartment.

132
Q
  1. Fire Protection

[] FIRE WHEEL WELL

A

Fire is detected in a main wheel well

133
Q
  1. Fire Protection

[] OVERHEAT ENG L, R

A

An overheat is detected in an engine.

134
Q
  1. Fire Protection

[] SMOKE REST UPR DR 1

A

Smoke is detected in the crew rest area.

135
Q
  1. Fire Protection

[] SMOKE REST UPR DR 5

A

Smoke is detected in the crew rest area.

136
Q
  1. Fire Protection

SMOKE OR FUMES REMOVAL

A

Smoke or fumes removal is needed

137
Q
  1. Flight Controls

[] STABILIZER (M)

A

One of these occurs:
• Stabilizer movement without a signal to trim;
• The stabilizer is failed.
(M)
1. STAB cutout switches (both)… CUTOUT;
2. Do not exceed the current airspeed.

138
Q
  1. Flight Controls

[] AUTO SPEEDBRAKE

A

An automatic speedbrake fault occurs.

NOTE: Do not arm the speedbrake lever. This prevents inadvertent in-flight speedbrake extension. Manually extend the speedbrakes after landing.

139
Q
  1. Flight Controls

[] FLAPS DRIVE

A

The flap drive mechanism is failed.

140
Q
  1. Flight Controls

[] FLAPS PRIMARY FAIL

A

The flaps primary mode is failed

141
Q
  1. Flight Controls

[] FLAP/SLAT CONTROL

A

The flap/slat electronics units are failed.

142
Q
  1. Flight Controls

[] FLIGHT CONTROL MODE

A

The flight control system is in the secondary mode.

143
Q
  1. Flight Controls

[] FLIGHT CONTROLS

A

One or more of these occurs:
• Two or more flight control surfaces are inoperative;
• Other faults in the flight control system are detected.

144
Q
  1. Flight Controls

FLT CONTROL VALVE

A

One or more of these occur:
• One or more of the flight control shutoff valves are failed closed;
• One or more of the flight control switches are in shutoff.

145
Q
  1. Flight Controls

JAMMED FLIGHT CONTROLS

A

Flight Controls are jammed or restricted in roll, pitch, or yaw.

146
Q
  1. Flight Controls

[] PITCH DOWN AUTHORITY

A

Pitch down authority is restricted.

Note: Slower airspeeds assist nosedown pitch control. The aeroplane is approaching it’s pitch down limit.

Avoid speedbrake use and rapid thrust increases in flight. Only limited elevator authority is available to counter nose up pitch.

Do not speed brake lever.

Slowly extend the speedbrakes after landing.

Refer to the non-normal configuration landing distance table in the performance in-flight chapter.

147
Q
  1. Flight Controls

[] PITCH UP AUTHORITY

A

Pitch up and flare authority are restricted.

148
Q
  1. Flight Controls

[] PRI FLIGHT COMPUTERS

A

The flight control system is operating in the direct mode.

149
Q
  1. Flight Controls

[] SLATS DRIVE

A

The slat drive mechanism is failed.

150
Q
  1. Flight Controls

[] SLATS PRIMARY FAIL

A

The slats primary mode is failed.

151
Q
  1. Flight Controls

SPEEDBRAKE EXTENDED

A

The speedbrakes are extended and one or more of these occur:
• The radio Altitude is between 15 and 800 feet;
• The flap lever is in a landing setting;
• A thrust lever is not at idle.

152
Q
  1. Flight Controls

[] SPOILERS

A

One or more spoiler pairs are failed.

Note: Roll rate may be reduced in flight. Speedbrake affectivness may be reduced in flight and during landing.

Roll tendencies, yaw tendencies, or airframe buffet can indicate a spoiler failed in the extended position. Do not use FMC fuel predictions with a spoiler panel extended.

153
Q
  1. Flight Controls

[] STAB GREENBAND

A

The nose gear pressure sensor disagrees with the computed stabiliser greenband.

154
Q
  1. Flight Controls

[] STABILIZER C

A

The Center stabiliser control path is failed.

155
Q
  1. Flight Controls

STABILIZER CUTOUT

A

Both Stabilizer cutout switches are in CUTOUT.

156
Q
  1. Flight Controls

[] STABILIZER R

A

The right Stabilizer control path is failed.

157
Q
  1. Flight Controls

[] THRUST ASYM COMP

A

Thrust asymmetry compensation is failed or off.

158
Q
  1. Flight Instruments, Displays

AIRSPEED UNRELIABLE (M)

A

Airspeed or Mach indications are suspected to be unreliable. (Items which can indicate unreliable airspeed are listed in the Additional Information section)
(M)
1. Autopilot disengage switch… Push;
2. A/T ARM switches (both)… OFF;
3. F/D switches (both)… OFF;
4. Set the following gear up pitch attitude and thrust:
• Flaps Extended… 10 deg/85% N1;
• Flaps Up…………. 4 deg/70% N1.

159
Q
  1. Flight Instruments, Displays

[] ALTN ATTITUDE

A

Both pilots AIR DATA/ATT source switches are in ALTN.

Note: Both PFDs show the SAARU attitude information.

160
Q
  1. Flight Instruments, Displays

BARO SET DISAGREE

A

The captains and first offices barometric settings disagree

161
Q
  1. Flight Instruments, Displays

[] CHKL INCOMPLETE NORM

A

A normal checklist needs to be completed

162
Q
  1. Flight Instruments, Displays

[] CHKL NON-NORMAL

A

There is a hidden nonnormal checklist. All of these occur:
• A non-normal checklist is not complete;
• The ECL is not displayed;
• The related EICAS message is not shown.

163
Q
  1. Flight Instruments, Displays

DISPLAY SELECT PNL

A

Left, Centre, or right CDU control of the display select panel is used.

164
Q
  1. Flight Instruments, Displays

[] EFIS CONTROL PNL L, R

A

One of these occurs:
• The EFIS control panel is failed;
• CDU control of the EFIS is used.

NOTE: Backup control of the EFIS is accessed from the CDU menu page.

165
Q
  1. Flight Instruments, Displays

SGL SOURCE AIR DATA

A

Both PFDs use the same air data source.

166
Q
  1. Flight Instruments, Displays

[] SGL SOURCE DISPLAYS

A

Some or all display units use a single source of display data.

Note: Both PFDs and NDs or just both NDs show information generated from a single source. The lower Center display unit may be blank or may not be capable of showing all normal formats. The left EFIS control panel controls either the right PFD and ND or the right ND only.

167
Q
  1. Flight Instruments, Displays

[] SGL SOURCE RAD ALT

A

Both PFDs use the same radio Altimeter source.

NOTE: A/T retard during flare is inoperative.

168
Q
  1. Flight Instruments, Displays

SINGLE SOURCE F/D

A

Both PFDs use the same flight director source.

169
Q
  1. Flight Management, Navigation

ADS-B OUT FAILURE

A

One or more of these occur:
• ATC reports ADS-B Out is lost or degraded;
• On the CDU POS REF 3/3 page, the GPS L line is blank and the left transponder is selected;
• On the CDU POS REF 3/3 page, the GPS R line is blank and the right transponder is selected.

170
Q
  1. Flight Management, Navigation

[] AIR DATA SYS

A

The three air data sources disagree.

171
Q
  1. Flight Management, Navigation

[] FMC

A

One of these occurs:
• The FMC selector is in L and the left FMC is failed;
• The FMC selector is in R and the right FMC is failed;
• Both FMCs are failed.

172
Q
  1. Flight Management, Navigation

FMC L, R

A

An FMC is failed.

173
Q
  1. Flight Management, Navigation

FMC MESSAGE

A

An alerting message is on the FMC scratchpad.

174
Q
  1. Flight Management, Navigation

[] GPS

A

Both GPS receivers are failed.

Note: The FMC uses inertial inputs only, unless radio updating is enabled.

ADS-B Out is inoperative.

If radio updating is allowed:
• Select the FMC REF NAV DATA page;
• Select OFF for RAD NAV INHIBIT.

175
Q
  1. Flight Management, Navigation

[] ILS ANTENNA

A

Two or more ILS receivers do not use the correct antenna.

Note: AFDS may have difficulty capturing or tracking localiser or glideslope. The airplane path may be lower than indicated by the glideslope pointer.

176
Q

[] INSUFFICIENT FUEL

A

FMC estimated fuel at the destination is less than the entered RESERVES fuel.

177
Q
  1. Flight Management, Navigation

[] NAV ADIRU INERTIAL

A

The ADIRU cannot supply correct attitude, position, heading, track, and ground speed data.

178
Q
  1. Flight Management, Navigation

[] NAV UNABLE RNP

A

The actual navigation performance is not sufficient.

179
Q
  1. Flight Management, Navigation

SINGLE SOURCE ILS

A

Both pilots’ displays use the same ILS source.

180
Q
  1. Flight Management, Navigation

TRANSPONDER L, R

A

A transponder fault occurs.

181
Q
  1. Flight Management, Navigation

[] VNAV STEP CLIMB

A

A FMC-predicted or manually-entered VNAV step climb point has been sequenced and the climb has not started.

182
Q
  1. Fuel

[] FUEL AUTO JETTISON

A

One of these occur:
• The total fuel quantity is less than or equal to the fuel to remain and a jettison nozzle valve is open;
• The fuel jettison automatic shutoff is failed.

183
Q
  1. Fuel

[] FUEL CROSSFEED AFT

A

The aft fuel crossfeed valve is not in the commanded position.

184
Q
  1. Fuel

[] FUEL CROSSFEED FWD

A

The forward fuel crossfeed valve is not in the commanded position.

185
Q
  1. Fuel

[] FUEL DISAGREE

A

The totaliser fuel quantity and the FMC calculated fuel quantity disagree.

186
Q
  1. Fuel

[] FUEL FLOW ENG L, R

A

Engine fuel flow is abnormally high.

187
Q
  1. Fuel

[] FUEL IMBALANCE

A

There is a fuel imbalance between the main tanks.

188
Q
  1. Fuel

FUEL IN CENTER

A

The Center tank fuel quantity is at the level where the pump switches must be ON.

189
Q
  1. Fuel

FUEL JETT NOZZLE L, R

A

A jettison nozzle valve is not in the commanded position.

190
Q
  1. Fuel

FUEL JETTISON

A

Fuel jettison is needed.

191
Q
  1. Fuel

[] FUEL JETTISON MAIN

A

The main tank fuel jettison system is failed.

192
Q
  1. Fuel

[] FUEL JETTISON SYS

A

The fuel jettison system is failed.

193
Q
  1. Fuel

FUEL LEAK

A

A fuel leak is suspected for the reasons listed in the Additional Information section of this checklist.

194
Q
  1. Fuel

FUEL LOW CENTER

A

The Center tank fuel quantity is at the level where the pump switches must be off.

195
Q
  1. Fuel

[] FUEL PRESS ENG L, R

A

The affected engine is on suction feed.

196
Q
  1. Fuel

FUEL PRESS ENG L+R

A

Fuel pressure to both engines is low on the ground with the engines shut down.

197
Q
  1. Fuel

[] FUEL PUMP CENTER L, R

A

The Center fuel pump pressure is low.

198
Q
  1. Fuel

[] FUEL PUMP L AFT, FWD

A

The left fuel pump pressure is low.

199
Q
  1. Fuel

[] FUEL PUMP R AFT, FWD

A

The right fuel pump pressure is low.

200
Q
  1. Fuel

[] FUEL QTY LOW

A

The fuel quantity is low in a main tank.

201
Q
  1. Fuel

[] FUEL SCAVENGE SYS

A

The fuel scavenge system is failed.

202
Q
  1. Fuel

[] FUEL TEMP LOW

A

Fuel temperature is near the minimum.

203
Q
  1. Fuel

[] FUEL VALVE APU

A

The APU fuel valve is not in the commanded position.

204
Q
  1. Hydraulics

[] HYD AUTO CONTROL C

A

Both of the following occur:
• Automatic control of both Center demand pumps fails;
• System indications fail.

205
Q
  1. Hydraulics

[] HYD AUTO CONTROL L, R

A

Both of the following occur:
• Automatic control of demand pump fails;
• System indications fail.

206
Q
  1. Hydraulics

[] HYD OVERHEAT DEM C1, C2, L, R

A

The pump temperature is high.

207
Q
  1. Hydraulics

[] HYD OVERHEAT PRI C1, C2

A

The pump temperature is high.

208
Q
  1. Hydraulics

[] HYD OVERHEAT PRI L, R

A

The pump temperature is high.

209
Q
  1. Hydraulics

[] HYD PRESS DEM C1, C2, L, R

A

The demand pump output pressure is low when commanded on.

210
Q
  1. Hydraulics

[] HYD PRESS PRI C1, C2

A

The pump pressure is low.

211
Q
  1. Hydraulics

[] HYD PRESS PRI L, R

A

The pump pressure is low.

212
Q
  1. Hydraulics

[] HYD PRESS SYS C

A

The Center hydraulic system pressure is low.

213
Q
  1. Hydraulics

[] HYD PRESS SYS L

A

The left hydraulic system pressure is low.

214
Q
  1. Hydraulics

[] HYD PRESS SYS L+C

A

The left and Center hydraulic systems pressures are low.

215
Q
  1. Hydraulics

HYD PRESS SYS L+C+R

A

All hydraulic system pressures are low.

216
Q
  1. Hydraulics

[] HYD PRESS SYS L+R

A

The left and right hydraulic system pressures are low.

217
Q
  1. Hydraulics

[] HYD PRESS SYS R

A

The right hydraulic system pressure is low.

218
Q
  1. Hydraulics

[] HYD PRESS SYS R+C

A

The right and Center hydraulic system pressures are low.

219
Q
  1. Hydraulics

[] HYD QTY LOW C

A

The Center hydraulic quantity is low.

220
Q
  1. Hydraulics

HYD QTY LOW L, R

A

The hydraulic quantity is low.

221
Q
  1. Hydraulics

[] HYD QTY LOW L+C

A

The left and Center hydraulic quantities are low.

222
Q
  1. Hydraulics

[] HYD QTY LOW L+C+R

A

All three hydraulic quantities are low.

223
Q
  1. Hydraulics

[] HYD QTY LOW L+R

A

The left and right hydraulic quantities are low.

224
Q
  1. Hydraulics

[] HYD QTY LOW R+C

A

The right and Center hydraulic quantities are low.

225
Q
  1. Hydraulics

RAT UNLOCKED

A

The ram air turbine is not stowed and locked.

226
Q
  1. Landing Gear

[] ANTISKID

A

An antiskid system fault occurs.

227
Q
  1. Landing Gear

AUTOBRAKE

A

One of these occurs:
• The autobrake system is disarmed;
• The autobrake system is failed.

228
Q
  1. Landing Gear

[] BRAKE SOURCE

A

Normal and alternate brake system pressures are low, and reserve hydraulic source for alternate brake system is low.

Note: Only accumulator pressure is available for braking. During landing rollout, apply steady, increasing brake pressure and hold to full stop. Do not taxi.

229
Q
  1. Landing Gear

[] BRAKE TEMP

A

One or more of the brake temperatures are high.

230
Q
  1. Landing Gear

[] GEAR DISAGREE

A

The gear position disagrees with the landing gear lever position.

231
Q
  1. Landing Gear

[] GEAR DOOR

A

One or more gear doors and not closed.

232
Q
  1. Landing Gear

GEAR LEVER LOCKED DOWN

A

The landing gear lever cannot move to UP.

233
Q
  1. Landing Gear

[] MAIN GEAR BRACE L, R

A

The main gear is down with one brace unlocked.

234
Q
  1. Landing Gear

MAIN GEAR STEERING

A

Main gear steering does not lock.

235
Q
  1. Landing Gear

[] RESERVE BRAKES/STRG

A

One or more of these are possibly not available:
• Alternate brakes from the reserve hydraulic source;
• Normal nose gear extension;
• Nose wheel steering.

note: Plan for possible alternate gear extension. Do not taxi with loss of steering.

236
Q
  1. Landing Gear

TAIL SKID

A

The tail skid is not in the commanded position.

237
Q
  1. Landing Gear

[] TIRE PRESSURES

A

One or more of the tire pressures are not normal.

238
Q
  1. Warning Systems

AIRSPEED LOW

A

Airspeed is less than minimum maneuvering speed.

239
Q
  1. Warning Systems

ALTITUDE ALERT

A

A deviations from the MCP set altitude occurs.

240
Q
  1. Warning Systems

ALTITUDE CALLOUTS

A

Altitude and minimums voice callouts during approach are not available.

241
Q
  1. Warning Systems

CONFIG DOORS

A

An entry, forward cargo, or aft cargo door is not closed and latched and locked during takeoff.

242
Q
  1. Warning Systems

CONFIG FLAPS

A

The flaps are not in the takeoff position during takeoff.

243
Q
  1. Warning Systems

CONFIG GEAR

A

A landing gear is not down and locked and one of these occurs:
• Below 800 feet radio altitude and a thrust lever is at or near idle;
• The flaps are in a landing position.

244
Q
  1. Warning Systems

CONFIG GEAR STEERING

A

Main gear steering is not locked during takeoff.

245
Q
  1. Warning Systems

CONFIG PARK BRAKE

A

The parking brake is set during takeoff.

246
Q
  1. Warning Systems

CONFIG RUDDER

A

Rudder trim is not centered during takeoff.

247
Q
  1. Warning Systems

CONFIG SPOILERS

A

One of these occurs:
• The speedbrake lever is not down during takeoff;
• The speedbrake lever is extended beyond ARMED in flight with climb thrust or greater.

248
Q
  1. Warning Systems

CONFIG STABILISER

A

The stabiliser is not in the greenband during takeoff.

249
Q
  1. Warning Systems

[] CONFIG WARNING SYS

A

A configuration warning system fault occurs.

250
Q
  1. Warning Systems

[] GRD PROX SYS

A

A ground proximity warning system fault occurs.

251
Q
  1. Warning Systems

OVERSPEED

A

Airspeed is more than Vmo/Mmo

252
Q
  1. Warning Systems

PILOT RESPONSE

A

Pilot action is not detected during a specified time.

253
Q
  1. Warning Systems

[] TAIL STRIKE

A

The tail hits the runway.

254
Q
  1. Warning Systems

[] TAIL STRIKE

A

A tail strike is suspected or confirmed.

255
Q
  1. Warning Systems

TCAS

A

TCAS is failed.

256
Q
  1. Warning Systems

TCAS OFF

A

TCAS modes TA or TA/RA are not selected.

257
Q
  1. Warning Systems

TCAS RA CAPTAIN, F/O

A

TCAS cannot show RA guidance on the PFD.

258
Q
  1. Warning Systems

TERR OVRD

A

The ground proximity terrain override switch is in OVRD.

259
Q
  1. Warning Systems

[] TERR POS

A

Terrain position data is lost.

Note: Position data for the ND terrain map and look-ahead terrain alerts are lost. Ground proximity alerts that occur are valid.

260
Q
  1. Warning Systems

[] WINDSHEAR SYS

A
  1. [] WINDSHEAR SYS

A windshear system fault occurs.

B777 FCOM (8 decks)

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