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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
1. Airplane General [] WINDOWS
1. [] WINDOWS The left and right side windows are not closed and secure
26
2. Air Systems [] CABIN ALTITUDE (M)
2. [] 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 ```
27
2. Air Systems BLEED ISLN CLOSED C, L, R
2. BLEED ISLN CLOSED C, L, R One of the following occurs: • the isolation valve has failed closed; • the bleed isolation switch is off
28
2. Air Systems BLEED ISLN OPEN C, L, R
2. BLEED ISLN OPEN C, L, R The isolation valve is failed open
29
2. Air Systems [] BLEED LEAK BODY
2. [] BLEED LEAK BODY A bleed air leak occurs in the body area
30
2. Air Systems [] BLEED LEAK L, R
2. [] BLEED LEAK L, R A bleed air leak occurs in the wing or pack bay area
31
2. Air Systems [] BLEED LEAK STRUT L, R
2. [] BLEED LEAK STRUT L, R A bleed air leak or starter duct leak occurs in the strut area.
32
2. Air Systems [] BLEED LOSS BODY
2. [] BLEED LOSS BODY Bleed air from the left and right body ducts is not available.
33
2. Air Systems [] BLEED LOSS BODY L
2. [] BLEED LOSS BODY L Bleed air from the left body duct is not available.
34
2. Air Systems [] BLEED LOSS BODY R
2. [] BLEED LOSS BODY R Bleed air from the right body duct is not available
35
2. Air Systems [] BLEED LOSS WING L, R
2. [] BLEED LOSS WING L, R Bleed air from the wing duct is not available
36
2. Air Systems BLEED OFF APU
2. 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.
37
2. Air Systems BLEED OFF ENG L, R
2. 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.
38
2. Air Systems [] CABIN ALTITUDE AUTO
2. [] CABIN ALTITUDE AUTO One of these occurs: • Automatic pressurisation control is failed; • Both outflow valve switches are in manual.
39
2. Air Systems CARGO HEAT AFT
2. CARGO HEAT AFT One of these occurs: • Aft lower cargo heat is inoperative; • The aft cargo temperature selector is OFF.
40
2. Air Systems CARGO HEAT BULK
2. CARGO HEAT BULK One of these occurs: • bulk cargo heat is inoperative; • the bulk cargo temperature selector is off.
41
2. Air Systems EQUIP COOLING
2. EQUIP COOLING The forward equipment cooling system is failed
42
2. Air Systems [] EQUIP COOLING OVRD
2. [] EQUIP COOLING OVRD The equipment cooling system is in override mode.
43
2. Air Systems [] LANDING ALTITUDE
2. [] LANDING ALTITUDE One of these occurs: • The FMC does not supply a landing altitude; • The landing altitude selector is pulled.
44
2. Air Systems [] OUTFLOW VALVE AFT, FWD
One of these occurs: • Automatic control of the outflow valve is inoperative; • The outflow valve switch is in manual.
45
2. Air Systems [] PACK L
The left pack is inoperative
46
2. Air Systems [] PACK L+R
Both packs are inoperative
47
2. Air Systems [] PACK MODE L, R
The pack is in the standby mode. Note: At lower altitudes or higher outside air temperatures, the pack may shut down.
48
2. Air Systems [] PACK R
The right pack is inoperative
49
2. Air Systems [] TRIM AIR L, R
The trim air valve is closed
50
3. Anti-Ice, Rain [] ANTI-ICE ENG L, R
The engine anti-ice valve is closed when commanded open
51
3. Anti-Ice, Rain [] ANTI-ICE LEAK ENG L, R
A bleed air leak occurs in the engine anti-ice duct
52
3. Anti-Ice, Rain ANTI-ICE LOSS ENG L, R
Anti-ice bleed air for the engine is not available
53
3. Anti-Ice, Rain [] ANTI-ICE ON
All of these occur: • wAn anti-ice selector is ON; • TAT is more than 10 degrees C; • Ice is not detected.
54
3. Anti-Ice, Rain [] ANTI-ICE WING
One or both wing anti-ice valves are failed closed.
55
3. Anti-Ice, Rain [] HEAT PITOT C
The Center pitot probe heat is failed. Note: The standby air data is unreliable in icing conditions.
56
3. Anti-Ice, Rain [] HEAT PITOT L
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.
57
3. Anti-Ice, Rain [] HEAT PITOT L+C+R
The left, Center and right pitot probe heat are failed. Note: The air data is unreliable in icing conditions.
58
3. Anti-Ice, Rain [] HEAT PITOT R
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.
59
3. Anti-Ice, Rain ICE CRYSTAL ICING
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)
60
3. Anti-Ice, Rain [] ICE DETECTORS
The ice detectors are failed. Note: Run the engine and wing anti-icing systems manually.
61
3. Anti-Ice, Rain ICING ENG
Ice is detected and an engine anti-ice selector is off.
62
3. Anti-Ice, Rain ICING WING
Icing is detected and one of these occurs: • The wing anti-ice selector is OFF; • The wing anti-ice takeoff inhibit is active.
63
3. Anti-Ice, Rain [] WINDOW HEAT L, R FWD
Primary window heat for the forward window is inoperative.
64
3. Anti-Ice, Rain [] WINDOW HEAT L, R SIDE
Window heat for the side window is inoperative
65
4. Automatic Flight AUTOPILOT
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.
66
4. Automatic Flight AUTOPILOT DISC
All autopilots are disengaged
67
4. Automatic Flight AUTOTHROTTLE DISC
Both autothrottles are disconnected
68
4. Automatic Flight [] AUTOTHROTTLE L, R
The Autothrottle is inoperative
69
4. Automatic Flight NO AUTOLAND
The autoland system is not available
70
4. Automatic Flight NO LAND 3
The autoland system does not have redundancy for a triple channel autoland
71
5. Communications DATALINK LOST
The ACARS datalink is temporarily lost
72
5. Communications DATALINK SYS
The datalink system is failed
73
5. Communications [] RADIO TRANSMIT
The microphone switch is on and causes a radio to transmit for 40 seconds or more.
74
5. Communications SATCOM
The SATCOM system is failed
75
5. Communications SATCOM DATALINK
The SATCOM datalink is failed
76
5. Communications SATCOM VOICE
SATCOM voice communication is failed
77
5. Communications SATVOICE LOST
SATCOM voice communication is temporarily lost
78
5. Communications VHF DATALINK
The VHF datalink is failed
79
6. Electrical [] ELEC AC BUS L, R
The AC Bus is not energised
80
6. Electrical [] ELEC BACKUP GEN L, R
The backup generator is failed
81
6. Electrical [] ELEC BACKUP SYS
The backup power system is failed
82
6. Electrical ELEC BATTERY OFF
The battery switch is off
83
6. Electrical ELEC BUS ISLN L, R
The bus tie breaker is open
84
6. Electrical ELEC CABIN/UTIL OFF
The cabin/utility power switch is OFF
85
6. Electrical [] ELEC GEN DRIVE L, R
A generator drive fault occurs
86
6. Electrical [] ELEC GEN OFF APU
The generator control breaker is open
87
6. Electrical [] ELEC GEN OFF L, R
The generator control breaker is open
88
6. Electrical ELEC GRD HDLG BUS
A fault occurs in the ground handling bus
89
6. Electrical ELEC IFE/SEATS OFF
The IFE/passenger seats power switch is OFF.
90
6. Electrical ELEC STANDBY SYS
A standby power system failure occurs
91
6. Electrical [] MAIN BATTERY DISCH
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.
92
7. Engines, APU ABORTED ENGINE START L, R (M)
On the ground, an aborted engine start is needed (M) 1. FUEL CONTROL switch (effected side)... CUTOFF
93
7. Engines, APU DUAL ENG FAIL/STALL (M)
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
94
7. Engines, APU [] ENG AUTOSTART L, R (M)
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.
95
7. Engines, APU ENG LIM/SURGE/STALL L, R (M)
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.
96
7. Engines, APU ENG SVR DAMAGE/SEP L, R (M)
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.
97
7. Engines, APU [] APU LIMIT
An APU limit exceedance occurs.
98
7. Engines, APU [] APU SHUTDOWN
An APU automatic shutdown occurs.
99
7. Engines, APU ENG AUTOSTART OFF
The engine autostart switch is off
100
7. Engines, APU ENG CONTROL L, R
An EEC system fault occurs.
101
7. Engines, APU [] ENG EEC MODE L, R
The EEC is in the alternate control mode
102
7. Engines, APU [] ENG FAIL L, R
Engine speed is below idle
103
7. Engines, APU [] ENG FUEL FILTER L, R
Fuel contamination can cause fuel to bypass the engine fuel filter.
104
7. Engines, APU [] ENG FUEL VALVE L, R
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.
105
7. Engines, APU ENG IDLE DISAGREE
One engine is at approach idle and the other is at minimum idle
106
7. Engines, APU ENG IN-FLIGHT START L, R
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
7. Engines, APU [] ENG LIMIT PROT L, R
The EEC is in the alternate mode and the commanded N1 exceeds the limit.
108
7. Engines, APU [] ENG OIL FILTER L, R
Oil filter contamination has caused oil to bypass the oil filter
109
7. Engines, APU [] ENG OIL PRESS L, R
The engine oil pressure is low
110
[] ENG OIL TEMP L,R
The engine oil temperature is high
111
7. Engines, APU [] ENG REV LIMITED L, R
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
7. Engines, APU ENG REVERSER L, R
A fault occurs in the thrust reverser system
113
7. Engines, APU ENG RPM LIMITED L, R
Engine thrust is at the N1 or N2 red line limit.
114
7. Engines, APU ENG SHUTDOWN
Both engines were shut down by the fuel control switches or the engine fire switches
115
7. Engines, APU ENG SHUTDOWN L, R
The engine was shutdown by the fuel control switch or the engine fire switch.
116
7. Engines, APU [] ENG START VALVE L, R
The start valve is not in the commanded position.
117
7. Engines, APU [] ENG STARTER CUTOUT L, R
One of these occurs: • The start valve fails to close; • The start selector stays in start.
118
7. Engines, APU ENG THRUST L, R
The engine thrust is less than the commanded thrust
119
7. Engines, APU VOLCANIC ASH
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
8. Fire Protection [] FIRE APU
Fire is detected in the APU
121
8. Fire Protection [] FIRE ENG L, R (M)
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
8. Fire Protection FIRE ENG TAILPIPE L, R
An engine tailpipe fire occurs on the ground with no fire warning.
123
8. Fire Protection SMOKE, FIRE OR FUMES
Smoke, fire or fumes occurs
124
8. Fire Protection BOTTLE 1, 2 DISCH ENG
The engine fire extinguisher bottle pressure is low
125
8. Fire Protection BOTTLE DISCH APU
The APU fire bottle pressure is low.
126
8. Fire Protection BOTTLE DISCH CARGO
Both rapid discharge cargo fire extinguisher bottle pressures are low
127
8. Fire Protection [] DET FIRE APU
APU fire detection is failed
128
8. Fire Protection DET FIRE CARGO AFT, FWD
Lower cargo compartment smoke detection is failed
129
8. Fire Protection DET FIRE ENG L, R
Engine fire and overheat detection is failed
130
8. Fire Protection [] FIRE CARGO AFT
Smoke is detected in the aft lower cargo compartment.
131
8. Fire Protection [] FIRE CARGO FWD
Smoke is detected in the forward lower cargo compartment.
132
8. Fire Protection [] FIRE WHEEL WELL
Fire is detected in a main wheel well
133
8. Fire Protection [] OVERHEAT ENG L, R
An overheat is detected in an engine.
134
8. Fire Protection [] SMOKE REST UPR DR 1
Smoke is detected in the crew rest area.
135
8. Fire Protection [] SMOKE REST UPR DR 5
Smoke is detected in the crew rest area.
136
8. Fire Protection SMOKE OR FUMES REMOVAL
Smoke or fumes removal is needed
137
9. Flight Controls [] STABILIZER (M)
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
9. Flight Controls [] AUTO SPEEDBRAKE
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
9. Flight Controls [] FLAPS DRIVE
The flap drive mechanism is failed.
140
9. Flight Controls [] FLAPS PRIMARY FAIL
The flaps primary mode is failed
141
9. Flight Controls [] FLAP/SLAT CONTROL
The flap/slat electronics units are failed.
142
9. Flight Controls [] FLIGHT CONTROL MODE
The flight control system is in the secondary mode.
143
9. Flight Controls [] FLIGHT CONTROLS
One or more of these occurs: • Two or more flight control surfaces are inoperative; • Other faults in the flight control system are detected.
144
9. Flight Controls FLT CONTROL VALVE
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
9. Flight Controls JAMMED FLIGHT CONTROLS
Flight Controls are jammed or restricted in roll, pitch, or yaw.
146
9. Flight Controls [] PITCH DOWN AUTHORITY
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
9. Flight Controls [] PITCH UP AUTHORITY
Pitch up and flare authority are restricted.
148
9. Flight Controls [] PRI FLIGHT COMPUTERS
The flight control system is operating in the direct mode.
149
9. Flight Controls [] SLATS DRIVE
The slat drive mechanism is failed.
150
9. Flight Controls [] SLATS PRIMARY FAIL
The slats primary mode is failed.
151
9. Flight Controls SPEEDBRAKE EXTENDED
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
9. Flight Controls [] SPOILERS
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
9. Flight Controls [] STAB GREENBAND
The nose gear pressure sensor disagrees with the computed stabiliser greenband.
154
9. Flight Controls [] STABILIZER C
The Center stabiliser control path is failed.
155
9. Flight Controls STABILIZER CUTOUT
Both Stabilizer cutout switches are in CUTOUT.
156
9. Flight Controls [] STABILIZER R
The right Stabilizer control path is failed.
157
9. Flight Controls [] THRUST ASYM COMP
Thrust asymmetry compensation is failed or off.
158
10. Flight Instruments, Displays AIRSPEED UNRELIABLE (M)
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
10. Flight Instruments, Displays [] ALTN ATTITUDE
Both pilots AIR DATA/ATT source switches are in ALTN. Note: Both PFDs show the SAARU attitude information.
160
10. Flight Instruments, Displays BARO SET DISAGREE
The captains and first offices barometric settings disagree
161
10. Flight Instruments, Displays [] CHKL INCOMPLETE NORM
A normal checklist needs to be completed
162
10. Flight Instruments, Displays [] CHKL NON-NORMAL
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
10. Flight Instruments, Displays DISPLAY SELECT PNL
Left, Centre, or right CDU control of the display select panel is used.
164
10. Flight Instruments, Displays [] EFIS CONTROL PNL L, R
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
10. Flight Instruments, Displays SGL SOURCE AIR DATA
Both PFDs use the same air data source.
166
10. Flight Instruments, Displays [] SGL SOURCE DISPLAYS
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
10. Flight Instruments, Displays [] SGL SOURCE RAD ALT
Both PFDs use the same radio Altimeter source. NOTE: A/T retard during flare is inoperative.
168
10. Flight Instruments, Displays SINGLE SOURCE F/D
Both PFDs use the same flight director source.
169
11. Flight Management, Navigation ADS-B OUT FAILURE
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
11. Flight Management, Navigation [] AIR DATA SYS
The three air data sources disagree.
171
11. Flight Management, Navigation [] FMC
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
11. Flight Management, Navigation FMC L, R
An FMC is failed.
173
11. Flight Management, Navigation FMC MESSAGE
An alerting message is on the FMC scratchpad.
174
11. Flight Management, Navigation [] GPS
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
11. Flight Management, Navigation [] ILS ANTENNA
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
[] INSUFFICIENT FUEL
FMC estimated fuel at the destination is less than the entered RESERVES fuel.
177
11. Flight Management, Navigation [] NAV ADIRU INERTIAL
The ADIRU cannot supply correct attitude, position, heading, track, and ground speed data.
178
11. Flight Management, Navigation [] NAV UNABLE RNP
The actual navigation performance is not sufficient.
179
11. Flight Management, Navigation SINGLE SOURCE ILS
Both pilots' displays use the same ILS source.
180
11. Flight Management, Navigation TRANSPONDER L, R
A transponder fault occurs.
181
11. Flight Management, Navigation [] VNAV STEP CLIMB
A FMC-predicted or manually-entered VNAV step climb point has been sequenced and the climb has not started.
182
12. Fuel [] FUEL AUTO JETTISON
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
12. Fuel [] FUEL CROSSFEED AFT
The aft fuel crossfeed valve is not in the commanded position.
184
12. Fuel [] FUEL CROSSFEED FWD
The forward fuel crossfeed valve is not in the commanded position.
185
12. Fuel [] FUEL DISAGREE
The totaliser fuel quantity and the FMC calculated fuel quantity disagree.
186
12. Fuel [] FUEL FLOW ENG L, R
Engine fuel flow is abnormally high.
187
12. Fuel [] FUEL IMBALANCE
There is a fuel imbalance between the main tanks.
188
12. Fuel FUEL IN CENTER
The Center tank fuel quantity is at the level where the pump switches must be ON.
189
12. Fuel FUEL JETT NOZZLE L, R
A jettison nozzle valve is not in the commanded position.
190
12. Fuel FUEL JETTISON
Fuel jettison is needed.
191
12. Fuel [] FUEL JETTISON MAIN
The main tank fuel jettison system is failed.
192
12. Fuel [] FUEL JETTISON SYS
The fuel jettison system is failed.
193
12. Fuel FUEL LEAK
A fuel leak is suspected for the reasons listed in the Additional Information section of this checklist.
194
12. Fuel FUEL LOW CENTER
The Center tank fuel quantity is at the level where the pump switches must be off.
195
12. Fuel [] FUEL PRESS ENG L, R
The affected engine is on suction feed.
196
12. Fuel FUEL PRESS ENG L+R
Fuel pressure to both engines is low on the ground with the engines shut down.
197
12. Fuel [] FUEL PUMP CENTER L, R
The Center fuel pump pressure is low.
198
12. Fuel [] FUEL PUMP L AFT, FWD
The left fuel pump pressure is low.
199
12. Fuel [] FUEL PUMP R AFT, FWD
The right fuel pump pressure is low.
200
12. Fuel [] FUEL QTY LOW
The fuel quantity is low in a main tank.
201
12. Fuel [] FUEL SCAVENGE SYS
The fuel scavenge system is failed.
202
12. Fuel [] FUEL TEMP LOW
Fuel temperature is near the minimum.
203
12. Fuel [] FUEL VALVE APU
The APU fuel valve is not in the commanded position.
204
13. Hydraulics [] HYD AUTO CONTROL C
Both of the following occur: • Automatic control of both Center demand pumps fails; • System indications fail.
205
13. Hydraulics [] HYD AUTO CONTROL L, R
Both of the following occur: • Automatic control of demand pump fails; • System indications fail.
206
13. Hydraulics [] HYD OVERHEAT DEM C1, C2, L, R
The pump temperature is high.
207
13. Hydraulics [] HYD OVERHEAT PRI C1, C2
The pump temperature is high.
208
13. Hydraulics [] HYD OVERHEAT PRI L, R
The pump temperature is high.
209
13. Hydraulics [] HYD PRESS DEM C1, C2, L, R
The demand pump output pressure is low when commanded on.
210
13. Hydraulics [] HYD PRESS PRI C1, C2
The pump pressure is low.
211
13. Hydraulics [] HYD PRESS PRI L, R
The pump pressure is low.
212
13. Hydraulics [] HYD PRESS SYS C
The Center hydraulic system pressure is low.
213
13. Hydraulics [] HYD PRESS SYS L
The left hydraulic system pressure is low.
214
13. Hydraulics [] HYD PRESS SYS L+C
The left and Center hydraulic systems pressures are low.
215
13. Hydraulics HYD PRESS SYS L+C+R
All hydraulic system pressures are low.
216
13. Hydraulics [] HYD PRESS SYS L+R
The left and right hydraulic system pressures are low.
217
13. Hydraulics [] HYD PRESS SYS R
The right hydraulic system pressure is low.
218
13. Hydraulics [] HYD PRESS SYS R+C
The right and Center hydraulic system pressures are low.
219
13. Hydraulics [] HYD QTY LOW C
The Center hydraulic quantity is low.
220
13. Hydraulics HYD QTY LOW L, R
The hydraulic quantity is low.
221
13. Hydraulics [] HYD QTY LOW L+C
The left and Center hydraulic quantities are low.
222
13. Hydraulics [] HYD QTY LOW L+C+R
All three hydraulic quantities are low.
223
13. Hydraulics [] HYD QTY LOW L+R
The left and right hydraulic quantities are low.
224
13. Hydraulics [] HYD QTY LOW R+C
The right and Center hydraulic quantities are low.
225
13. Hydraulics RAT UNLOCKED
The ram air turbine is not stowed and locked.
226
14. Landing Gear [] ANTISKID
An antiskid system fault occurs.
227
14. Landing Gear AUTOBRAKE
One of these occurs: • The autobrake system is disarmed; • The autobrake system is failed.
228
14. Landing Gear [] BRAKE SOURCE
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
14. Landing Gear [] BRAKE TEMP
One or more of the brake temperatures are high.
230
14. Landing Gear [] GEAR DISAGREE
The gear position disagrees with the landing gear lever position.
231
14. Landing Gear [] GEAR DOOR
One or more gear doors and not closed.
232
14. Landing Gear GEAR LEVER LOCKED DOWN
The landing gear lever cannot move to UP.
233
14. Landing Gear [] MAIN GEAR BRACE L, R
The main gear is down with one brace unlocked.
234
14. Landing Gear MAIN GEAR STEERING
Main gear steering does not lock.
235
14. Landing Gear [] RESERVE BRAKES/STRG
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
14. Landing Gear TAIL SKID
The tail skid is not in the commanded position.
237
14. Landing Gear [] TIRE PRESSURES
One or more of the tire pressures are not normal.
238
15. Warning Systems AIRSPEED LOW
Airspeed is less than minimum maneuvering speed.
239
15. Warning Systems ALTITUDE ALERT
A deviations from the MCP set altitude occurs.
240
15. Warning Systems ALTITUDE CALLOUTS
Altitude and minimums voice callouts during approach are not available.
241
15. Warning Systems CONFIG DOORS
An entry, forward cargo, or aft cargo door is not closed and latched and locked during takeoff.
242
15. Warning Systems CONFIG FLAPS
The flaps are not in the takeoff position during takeoff.
243
15. Warning Systems CONFIG GEAR
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
15. Warning Systems CONFIG GEAR STEERING
Main gear steering is not locked during takeoff.
245
15. Warning Systems CONFIG PARK BRAKE
The parking brake is set during takeoff.
246
15. Warning Systems CONFIG RUDDER
Rudder trim is not centered during takeoff.
247
15. Warning Systems CONFIG SPOILERS
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
15. Warning Systems CONFIG STABILISER
The stabiliser is not in the greenband during takeoff.
249
15. Warning Systems [] CONFIG WARNING SYS
A configuration warning system fault occurs.
250
15. Warning Systems [] GRD PROX SYS
A ground proximity warning system fault occurs.
251
15. Warning Systems OVERSPEED
Airspeed is more than Vmo/Mmo
252
15. Warning Systems PILOT RESPONSE
Pilot action is not detected during a specified time.
253
15. Warning Systems [] TAIL STRIKE
The tail hits the runway.
254
15. Warning Systems [] TAIL STRIKE
A tail strike is suspected or confirmed.
255
15. Warning Systems TCAS
TCAS is failed.
256
15. Warning Systems TCAS OFF
TCAS modes TA or TA/RA are not selected.
257
15. Warning Systems TCAS RA CAPTAIN, F/O
TCAS cannot show RA guidance on the PFD.
258
15. Warning Systems TERR OVRD
The ground proximity terrain override switch is in OVRD.
259
15. Warning Systems [] TERR POS
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
15. Warning Systems [] WINDSHEAR SYS
15. [] WINDSHEAR SYS A windshear system fault occurs.

B777 FCOM (8 decks)

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