Condition Statements Flashcards
1
Q
Bomb on Board
A
Condition: Bomb threat received from ground or cabin, or suspicious article is found on board.
2
Q
Chemical / Biological or
HAZMAT / Dangerous Goods Threat
A
Condition: One of these occur
- Hazardous material (chemical or biological threat) received from the ground or cabin
- Dangerous goods threat
- Reports of unknown multiple cabin illness
3
Q
Ditching
A
Condition: Aircraft ditching and evacuation are needed
4
Q
Precautionary Disembarkation
A
Condition: The situation requires the orderly but rapid disembarkation of the passengers and crew
5
Q
AUTOMATIC UNLOCK
A
Condition: The correct emergency access code is entered
Objective: To deny unauthorised access to the flight before the door automatically unlocks.
6
Q
CARGO DOOR
A
Condition: One or more cargo doors are not closed and secure
7
Q
ELT
A
Condition: The emergency locator transmitter is on
8
Q
EMERGENCY EXIT LIGHTS NOT ARMED
A
Condition: The emergency exit lights switch is not ARMED
9
Q
ENTRY DOOR
A
Condition: One or more entry door are not closed and secure
10
Q
EQUIPMENT DOOR
A
Condition: The equipment door is not closed and secure
11
Q
LOCK FAIL
A
Condition: One or more of these occur
- The FLIGHT DECK ACCESS SYSTEM switch is off
- The lock failed
Objective: To remove electrical power from the lock to prevent possible overheat
12
Q
OVERWING DOOR
A
Condition: One or more service doors are not closed and secure
13
Q
PASSENGER OXYGEN ON
A
Condition: The passenger oxygen system is on
14
Q
SERVICE DOOR
A
Condition: One or more of the service doors are not closed and secure
15
Q
Window Damage - Forward
L1, L2, R1, R2
A
Condition: A forward flight deck window has one or more of these
- An electrical arc
- A delamination
- A crack
- Is shattered
Objective: To remove electrical power, if needed, to prevent arcing. To reduce differential pressure and descend if the inner pane is shattered of cracked.
16
Q
Window Damage - Unheated Side
L3, R3
A
Condition: An unheated side flight deck window has one or more of these:
- A crack
- Is shattered
Objective: To reduce differential pressure to 0 psi if both panes are shattered or cracked.
17
Q
Window Noise
A
Condition: Excessive noise from a number 2 flight deck window seal.
18
Q
Window Open
A
Condition: A side window opens during takeoff or in flight.
19
Q
CABIN ALTITUDE WARNING
or
Rapid Depressurisation
A
Condition: One or more of these occur
- A cabin altitude exceedance
- In flight, the intermittent cabin altitude/configuration warning horn sounds or the CABIN ALTITUDE light (if installed and operative) illuminates.
20
Q
AUTO FAIL
or
Unscheduled Pressurization Change
A
Condition: One or more of these occur
- Automatic pressurization mode has failed
- The cabin altitude is uncontrollable
Objective: To maintain control of the cabin altitude
21
Q
BLEED TRIP OFF
A
Condition: One or more of these occur
- An engine bleed air overheat
- An engine bleed air overpressure
22
Q
Cabin Temperature Hot
A
Condition: Flight deck or passenger cabin temperature is excessively hot. The temperature can cause incapacitation.
Objective: To regain temperature control. If unable to regain control, to descend and configure to provide alternate ventilation.
23
Q
DUAL BLEED
A
Condition: The APU bleed valve is open and one of these occurs
- BLEED 1 air switch is on
- BLEED 2 air switch is on and the ISOLATION VALVE is open
Objective: To prevent possible back pressure of the APU.
24
Q
EQUIPMENT COOLING OFF
A
Condition: The equipment cooling supply or exhaust fan is failed
25
OFF SCHEDULE DESCENT
Condition: A descent is started before reaching the planned cruise altitude set in the FLT ALT indicator.
26
PACK
Condition: One or more of these occur
- The primary and standby pack controls are failed
- A pack overheat.
27
WING-BODY OVERHEAT
Condition: An overheat from a bleed duct leak occurs
Objective: To isolate the bleed duct leek
28
ZONE TEMP
Condition: One or more of these occur
- A zone duct overtemp
- Flight deck temperature control is failed.
29
Emergency Descent
Condition: One or more of these occur
- Cabin altitude cannot be controlled
- A rapid descent is needed.
30
ENGINE COWL ANTI-ICE
Condition: An engine cowl anti-ice duct overpressure occurs.
Objective: To reduce cowl duct pressure by reducing thrust
31
ENGINE COWL VALVE OPEN OR TAI INDICATION
Condition: One or both of the following occurs
- An engine COWL VALVE OPEN light stays illuminated bright blue
- An amber TAI indication is shown.
32
Ice Crystal Icing
Condition: Engine ice crystal 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 returns below the airplane
- Appearance of liquid water on the windshield at temperatures too cold for rain (the sound is different than rain)
- The autothrottle is unable to maintain selected airspeed
- TAT indication stays near 0*C
(Additional items that indicate ice crystal icing are listed in the Additional Information section)
Objective: To exit the ice crystal icing conditions and reduce the operational effects of the icing
33
PROBE HEAT
Condition: One or more probe heats are failed
34
WINDOW OVERHEAT
Condition: A window overheat occurs
35
WING ANTI-ICE VALVE OPEN
Condition: A wing anti-ice L VALVE OPEN or R VALVE OPEN light stays illuminated bright blue. The wing anti-ice valve is not in the commanded position.
36
AUTOPILOT DISENGAGE
Condition: All autopilots are disengaged. The red light flashes and the aural tone sounds.
37
AUTOTHROTTLE DISENGAGE
Condition: The autothrottle is disengaged. The red light flashes.
38
ACARS Electrical Power Loss
Condition: The ACARS AC power is lost.
39
ACARS MU Fail or DU Fail
Condition: The ACARS system is failed.
40
Radio Transmit Continuous
| Stuck Microphone Switch
Condition: A radio transmits continuously without crew input.
41
BATTERY DISCHARGE
Condition: A battery discharge exceedance occurs.
42
DRIVE
Condition: A generator drive malfunction occurs.
43
ELEC
Condition: A standby power or DC system fault occurs.
44
LOSS OF BOTH ENGINE DRIVEN GENERATORS
Condition: Both engine driven generators are off.
45
SOURCE OFF
Condition: The transfer bus is not powered by the last selected source.
46
STANDBY POWER OFF
Condition: One or more of these buses are not energised.
- AC Standby bus
- DC Standby bus
- Battery bus.
47
TR UNIT
Condition: One or more of the transformer rectifiers are failed.
48
TRANSFER BUS OFF
Condition: The transfer bus is not energised.
49
Aborted Engine Start
Condition: On the ground, an aborted engine start is needed.
Objective: To shut down the engine and motor it.
50
Engine Limit or Surge or Stall
Condition: One or more of these occur
- Engine indications are abnormal
- Engine indications are rapidly approaching or exceeding limits
- 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 inlet or exhaust are reported.
Objective: To attempt to recover normal engine operation or shut down the engine if recovery is not possible.
51
Loss Of Thrust On Both Engines
Condition: Both of these occur
- Both engines have a loss of thrust
- Both ENG FAIL alerts show.
Objective: To restart at least one engine
52
APU FAULT
Condition: An APU malfunction occurs.
53
APU LOW OIL PRESSURE
Condition: The APU pressure is low.
54
APU OVERSPEED
Condition: One of these occurs
- An APU RPM limit exceedance causes automatic shutdown
- During normal APU shutdown the overspeed shutdown protection logic fails a self-test
55
EEC ALTERNATE MODE
Condition: An EEC operates in the alternate control mode.
56
ENGINE CONTROL
Condition: An engine control system fault occurs.
57
Engine Failure or Shutdown
Condition: One of these occurs
- An engine failure
- An ENG FAIL alert is shown
- An engine flameout
- Another checklist directs an engine shutdown.
58
Engine High Oil Temperature
Condition: The engine oil temperature is high.
59
Engine High Vibration
Condition: The vibration is more than 4.0 units. Airframe vibration may or may not be felt.
60
Engine In-Flight Start
Condition: An engine is needed and all of the following are true
- There was no engine fire
- There is N1 rotation
- There is no abnormal airframe vibration.
61
ENGINE LOW OIL PRESSURE
Condition: The engine oil pressure is low. The LOW OIL PRESSURE alert may or may not be illuminated.
62
ENGINE OIL FILTER BYPASS
Condition: The OIL FILTER BYPASS alert indicates oil filter contamination can cause oil to bypass the oil filter.
63
One Engine Inoperative Landing
Condition: Landing must be made with one engine inoperative.
64
REVERSER
Condition: A fault occurs in the thrust reverser system.
65
REVERSER UNLOCKED (IN FLIGHT)
Condition: The amber REV indication shows with uncommanded reverse thrust.
66
START VALVE OPEN
Condition: The START VALVE OPEN alert indicates the start valve fails to close.
67
Volcanic Ash
Condition: Volcanic ash is suspected when one or more of these occur
- A static discharge around the windshield
- A bright static glow in the engine inlets
- Smoke or dust on the flight deck
- An acrid odour.
Objective: To exit the ash cloud and restart the engines if needed.
68
APU FIRE
Condition: Fire is detected in the APU.
69
ENGINE FIRE
or
Engine Severe Damage or Separation
Condition: One or more of these occur:
- Engine fire warning
- Airframe vibrations with abnormal engine indications
- Engine separation.
70
ENGINE OVERHEAT
Condition: An overheat is detected in the engine
71
Engine Tailpipe Fire
Condition: An engine tailpipe fire occurs on the ground with no engine fire warning.
72
Smoke, Fire or Fumes
Condition: Smoke, fire or fumes occur.
73
APU DETECTION INOPERATIVE
Condition: APU fire detection is inoperative.
74
CARGO FIRE
Condition: Fire is detected in the related cargo compartment.
75
CARGO FIRE DETECTOR FAULT
Condition: Fire detection is inoperative in one or both cargo compartments.
76
ENGINE FIRE/OVERHEAT DETECTOR FAULT
Condition: Engine fire and overheat detection is inoperative.
77
LAVATORY SMOKE
Condition: Smoke is detected in one or more lavatories.
78
Smoke or Fumes Removal
Condition: Smoke or fumes removal is needed.
79
WHEEL WELL FIRE
Condition: Fire is detected in the main wheel well.
80
Runaway Stabilizer
Condition: Uncommanded stabilizer trim movement occurs continuously.
81
All Flaps Up Landing
Condition: The leading edge devices fail to extend and trailing edge flaps are less than 1.
Objective: To configure for a landing with the leading edge devices retracted and trailing edge flaps less than 1.
82
AUTO SLAT FAIL
Condition: The auto slat system is failed.
83
Elevator Tab Vibration
Condition: An elevator tab vibration occurs in flight.
One or more of the following may be an indication of an elevator tab vibration:
- Vibration that originates, and is strongest, in the aft part of the aircraft but can be felt throughout the aircraft
- Vibration that is felt in the control wheel and rudder pedals
- Vibration that causes items attached to the aircraft, such as sun visors, to move.
84
FEEL DIFFERENTIAL PRESSURE
Condition: High differential pressure is measured by the elevator feel computer.
85
FLIGHT CONTROL LOW PRESSURE
Condition: Hydraulic system pressure to the ailerons, elevators and rudder is low.
Objective: To activate the standby hydraulic system and standby rubber PCU.
86
Jammed or Restricted Flight Controls
Condition: A flight control is jammed or restricted in roll, pitch or yaw.
87
LEADING EDGE FLAPS TRANSIT
Condition: One or more of these occur:
- The leading edge devices are not in the commanded position.
- A leading edge device asymmetry is detected
- A leading edge device skew is detected.
88
MACH TRIM FAIL
Condition: The Mach trim system is failed.
89
SPEED BRAKE DO NOT ARM
Condition: An automatic speedbrake fault occurs.
90
SPEED TRIM FAIL
Condition: The speed trim system is failed.
91
SPEEDBRAKES EXTENDED
Condition: In flight, the speedbrakes are extended beyond the ARMED position and one or more of these occur:
- The radio altitude is below 800 feet
- The flap lever setting is more than flaps 10.
On the ground, the SPEED BRAKE lever is down and the speedbrakes are extended.
92
STABILIZER OUT OF TRIM
Condition: The autopilot does not set the stabilizer trim correctly.
93
Stabilizer Trim Inoperative
Condition: Both of these occur:
- Loss of electric trim through the autopilot
- Loss of electric trim through the control wheel switches.
Objective: To land the airplane using manual trim or, if manual trim is not available, to land the airplane using elevator control only.
94
STANDBY RUDDER ON
Condition: The standby rudder hydraulic system is commanded on.
95
Trailing Edge Flap Asymmetry
Condition: One or more of these occur:
- An uncommanded roll occurs when the flaps change position
- The left and right flap indicators disagree.
Objective: To configure the airplane for landing.
96
Trailing Edge Flap Disagree
Condition: The trailing edge flaps are not in the commanded position.
Objective: To configure the aircraft for landing.
97
Trailing Edge Flaps Up Landing
Condition: The trailing edge flaps are less than 1.
Objective: To configure for a landing with trailing edge flaps less than 1.
98
YAW DAMPER
Condition: The yaw damper is disengaged.
99
Airspeed Unreliable
Condition: Airspeed or Mach indications are suspected to be unreliable. (Items which might indicate unreliable airspeed are listed in the Additional Information section)
Objective: To identify a reliable airspeed indication, if possible, or to continue the flight using the Flight with Unreliable Airspeed table in the Performance Inflight chapter.
100
ALT DISAGREE
Condition: The ALT DISAGREE alert indicates the captain's and first officer's altitude indications disagree by more than 200ft.
101
AOA DISAGREE
Condition: The AOA DISAGREE alert indicates the left and right angle of attack vanes disagree
102
CDS FAULT
Condition: The CDS FAULT annunciation indicates a CDS fault occurs.
103
Display Failure
Condition: A display in the common display system is failed.
104
DISPLAYS CONTROL PANEL
Condition: The DISPLAYS CONTROL PANEL annunciation indicates the EFIS control panel is failed.
105
DISPLAY SOURCE
Condition: The DISPLAY SOURCE annunciation indicates only one DEU is supplying display information. Indications may include:
- No hydraulic pressure indication on the failed side
- Speed limit flag shown on the failed side
- Minimum manoeuvre speed and stick shaker band removed on the failed side
- Both EEC ALTN lights illuminated.
106
FLIGHT RECORDER OFF
Condition: The flight recorder is off.
107
IAS DISAGREE
Condition: The IAS DISAGREE alert indicates the captain's and first officer's airspeed indications disagree.
108
ADS-B Out Failure
Condition: One or more of these occur:
- ATC reports ADS-B Out is lost or degraded
- GPS-L or GPS-R INVALID message is in the FMC scratchpad and the transponder is selected to the related side.
109
FMC DISAGREE
Condition: Data needed for dual FMC operation disagree.
110
FMC DISAGREE - VERTICAL
Condition: One of the following occur:
- Left FMC and right FMC target airspeed disagree during descent
- Left FMC and right FMC vertical paths disagree during descent.
111
FMC FAIL
Condition: Display of VTK followed by MAP failure flags on one or both navigation displays.
Objective: To restore dual FMC operation, configure for single FMC operation or resume conventional navigation.
112
FMC/CDU ALERTING MESSAGE
Condition: An alert message is in the FMC scratchpad.
113
GLS
Condition: A GLS failure occurs.
114
GPS
Conditions: Both GPS receivers are failed.
115
ILS
Conditions: An ILS failure occurs.
116
IRS DC FAIL
Conditions: IRS backup DC power is failed.
117
IRS FAULT
Conditions: One or more of these occur:
- An IRS fault occurs
- On the ground, if the ALIGN light is also illuminated, the present position entry is possibly incorrect.
118
IRS ON DC
Conditions: IRS AC power is failed.
119
RVSM Contingency Procedures
Condition: Unable to meet RVSM requirements.
120
UNABLE REQD NAV PERF - RNP
Condition: UNABLE REQD NAV PERF - RNP is shown. The actual navigation performance is not sufficient.
121
CONFIG
Condition: All of these occur:
- Both centre tank fuel pump switches are off
- There is more than 726 kgs of fuel in the centre tank.
- An engine is running.
122
CROSSFEED SELECTOR INOPERATIVE
Condition: One of the following occurs:
- The crossfeed VALVE OPEN light stay illuminated bright blue
- The CROSSFEED selector is in the open position and the crossfeed VALVE OPEN light is extinguished
- When the CROSSFEED selector is rotated to a new position, the crossfeed VALVE OPEN light does not illuminate bright blue.
123
FUEL FILTER BYPASS
Condition: Fuel contamination can cause fuel to bypass the engine fuel filter.
124
Fuel Leak Engine
Condition: An engine fuel leak is suspected for the reasons listed in the Additional Information section of this checklist.
Objective: To confirm there is an engine fuel leak and shut down the affected engine if needed. This checklist does not address the unlikely possibility of a tank leak.
125
FUEL PUMP LOW PRESSURE
Condition: The fuel pump pressure is low.
126
Fuel Quantity Indication Inoperative
Condition: The fuel quantity indication is blank.
127
Fuel Temperature Low
Condition: The fuel temperature is near the minimum.
128
IMBAL
Condition: There is a fuel imbalance between the main tanks.
Objective: To decide if a fuel leak is suspected. To balance fuel if a fuel leak is not suspected.
129
LOW
Condition: The fuel quantity is low in the main tank
Objective: To decide is a fuel leak is suspected. To ensure that all fuel is available for use.
130
HYDRAULIC PUMP LOW PRESSURE
Condition: The hydraulic pump pressure is low
131
HYDRAULIC PUMP OVERHEAT
Condition: The hydraulic pump temperature is high.
132
LOSS OF SYSTEM A
Condition: Hydraulic system A pressure is low.
133
LOSS OF SYSTEM B
Condition: Hydraulic system B pressure is low
134
MANUAL REVERSION
or
LOSS OF SYSTEM A AND SYSTEM B
Condition: Hydraulic system A and B pressure are low.
135
STANDBY HYDRAULIC LOW PRESSURE
Condition: The standby hydraulic pump pressure is low.
136
STANDBY HYDRAULIC LOW QUANTITY
Condition: The standby hydraulic quantity is low.
137
ANTISKID INOPERATIVE
Condition: An antiskid system fault occurs.
138
AUTO BRAKE DISARM
Condition: The autobrake system disarms after being set.
139
Brake Pressure Indicator Zero PSI
Condition: The brake accumulator has no nitrogen precharge.
140
GEAR DISAGREE
Condition: The landing gear position disagrees with the LANDING GEAR lever position.
141
Landing Gear Lever Jammed in the Up Position
Condition: The LANDING GEAR lever will not move from the UP position.
142
Landing Gear Lever Will Not Move Up After Takeoff
Condition: The LANDING GEAR lever cannot be moved to the UP position due to one of the following:
- Failure of the landing gear lever lock solenoid
- Failure of the air/ground system
- Failure of the ground spoiler bypass valve to close.
143
Manual Gear Extension
Condition: One of these occurs:
- Any landing gear is not down and locked when the LANDING GEAR lever is down
- The LANDING GEAR lever is jammed in the OFF position.
144
Partial or All Gear Up Landing
Condition: All landing gear are not down and locked after attempting manual gear extension.
145
LANDING CONFIGURATION
Condition: In flight, the steady warning horn sounds.
146
TAKEOFF CONFIGURATION
Condition: On the ground, the intermittent cabin altitude/configuration warning horn sounds or a TAKEOFF CONFIG light (if installed and operative) illuminates when advancing the thrust levers to takeoff thrust.
147
WARNING HORN (INTERMITTENT)
or
WARNING LIGHT - CABIN ALTITUDE OR TAKEOFF CONFIGURATION
Condition: One of these occurs:
- In flight, at an airplane flight altitude above 10,000 feet MSL, the intermittent warning horn or a CABIN ALTITUDE light (if installed and operative) illuminates
- On the ground, the intermittent warning horn sounds or a TAKEOFF CONFIG light (if installed and operative) illuminates when advancing the thrust levers to takeoff thrust.
148
GROUND PROXIMITY INOPERATIVE
Condition: A ground proximity warning system fault occurs.
149
Overspeed
Condition: Airspeed is more than Vmo/Mmo.
150
PSEU
Condition: A proximity switch electronics unit fault occurs.
151
Tail Strike
Condition: A tail strike is suspected or confirmed.
