Memory Items cockpit/flows Flashcards
1
Q
- OXYGEN panel
What does the illumination of the SYS ON light mean?
A
The signal has been sent to release the oxygen mask doors
2
Q
- OXYGEN panel
Does this mean that the masks have all deployed?
A
No - some masks may have to be deployed manually
3
Q
- OXYGEN panel
What causes automatic deployment of the masks?
A
Cabin Altitude reaching approximately 14,000 feet
4
Q
- OXYGEN panel
How does the passenger oxygen system work?
A
Chemical oxygen generators for approximately 15 minutes
5
Q
- OXYGEN panel
What happens when a pilot pushes the CREW SUPPLY PB?
A
Valve opens to supply low pressure crew oxygen
6
Q
- RCDR Panel
Why is the GND CTL PB selected to ON during preflight?
A
To record preflight activities in the cockpit
7
Q
- RCDR Panel
If the PB was not selected ON, how would the system work in automatic mode?
A
ON for 5 minutes after electrical power is supplied to the aircraft
At least one engine is operating, stops 5 min after last engine shut down.
8
Q
- RCDR Panel
What allows the cabin PA’s to be recorded?
A
ACP 3 PA Volume knob out and in 12 o’clock position
9
Q
- EMER ELEC PWR Panel
What is the significance of the red FAULT illuminating on the RAT & EMER GEN
light?
A
AC BUS1 and AC BUS 2 are lost and the RAT is not supplying electrical power
10
Q
- EMER ELEC PWR Panel
When would it normally illuminate?
A
During the 8-second RAT deployment
11
Q
- EMER ELEC PWR Panel
How can the RAT be deployed?
A
Manually by pushing MAN ON or RAT MAN ON, or Automatically by the loss of both AC
BUS 1 and AC BUS 2
12
Q
- EMER ELEC PWR Panel
What does the RAT supply?
A
Blue Hydraulic system and the emergency electrical generator
13
Q
- EMER ELEC PWR Panel
What buses are powered by the emergency electrical generator?
A
AC ESS and AC ESS Shed
DC ESS and DC ESS shed
14
Q
- EMER ELEC PWR Panel
What is the difference between the Automatic RAT deployment and RAT deployed by
pressing the RAT MAN ON on the HYD panel?
A
RAT MAN ON supplies Blue Hydraulic PSI only, no electrical generation
15
Q
- EMER ELEC PWR Panel
After deploying the RAT by pressing the RAT MAN ON pushbutton on the HYD panel
and it became necessary to also extract electrical power, how it be accomplished?
A
By pressing the MAN ON pushbutton on the EMER ELEC PWR
16
Q
- EMER ELEC PWR Panel
What would cause the GEN 1 LINE SMOKE light to illuminate?
A
Smoke detected in the avionics ventilation ducting
17
Q
- EMER ELEC PWR Panel
ECAM procedure directs the GEN 1 LINE PB to OFF. What is accomplished?
A
Gen 1 line contactor opens (white OFF light illuminates)
AC BUS 1 powered by GEN 2 through the Bus Tie Contactor
Gen 1 powers one fuel pump directly in each wing tank
18
Q
- FLIGHT CONTROLS
What type of flight control system does the A320 family aircraft utilize?
A
Fly-By-Wire System
19
Q
- FLIGHT CONTROLS
How are they controlled and activated?
A
Electrically and Hydraulically, respectively
20
Q
- FLIGHT CONTROLS
How is NORMAL LAW indicated on the PFD?
A
Green double markers
21
Q
- FLIGHT CONTROLS
How is ALTERNATE LAW indicated on the PFD?
A
Amber X’s (indicating lack of NORMAL LAW protections)
22
Q
- FLIGHT CONTROLS
How is DIRECT LAW indicated on the PFD?
A
AMBER “USE MANUAL PITCH TRIM”
Amber X’s (indicating lack of NORMAL LAW protections)
23
Q
- FLIGHT CONTROLS
How is MECHANICAL BACKUP indicated on the PFD?
A
RED “MAN PITCH TRIM ONLY”
Amber X’s (indicating lack of NORMAL LAW protections)
24
Q
- FLIGHT CONTROLS
When operating in NORMAL LAW in FLIGHT mode, what does the side stick command for pitch and roll?
A
Pitch – G load
Bank – Roll Rate
25
4. FLIGHT CONTROLS
What is the significance of the Side Stick Priority (Red Arrow) Light?
The other pilot has gained side stick authority
26
4. FLIGHT CONTROLS
Name the Flight Control Computers
ELAC – Elevator Aileron Computer (2)
SEC – Spoiler Elevator Computer (3)
FAC – Flight Augmentation Computer (2)
27
4. FLIGHT CONTROLS
What are the some of the ELAC functions? QRM should be referenced.
Normal elevator
Normal aileron
Normal pitch and roll
Alternate pitch
Direct pitch and roll
Abnormal alt
Aileron droop
Autopilot orders
28
4. FLIGHT CONTROLS
What are some of the SEC functions? QRM should be referenced.
Normal roll
Speed brakes
Alternate pitch
Direct pitch
Direct roll
Abnormal altitude
29
4. FLIGHT CONTROLS
What does the SEC 3 control?
Spoiler Control – one flight spoiler and one ground spoiler on each wing
30
4. FLIGHT CONTROLS
What are some of the FAC functions?
Rudder Trim
Rudder travel limit
Yaw control
Flight Envelope Protection - vertical
Windshear Protection
Low Energy Warning Protection
Alpha Floor Protection
PFD speed scale
31
4. FLIGHT CONTROLS
What should happen to the THS after landing?
Reset to zero
32
4. FLIGHT CONTROLS
Explain the spoiler extension logic on landing
For full extension:
Less than six feet RA + both struts compressed OR
More than 72 KT wheel speed on both wheels
Thrust at idle – above ten feet RA = TLA < 4 / below ten feet RA = TLA < 15
If NOT armed, they will extend when at least one engine TLA = REVERSE For partial extension (ten degrees):
One engine at reverse with the other at idle and one main landing gear strut compressed
33
4. FLIGHT CONTROLS
Explain the spoiler extension logic on a rejected takeoff
If the spoilers are armed, and speed exceeds 72 KT, they extend fully when both TLA = IDLE
If the spoilers are not armed, and speed exceeds 72 KT, they extend fully when one TLA = REVERSE
34
5. ADIRS
What is the ADIRS?
Air Data and Inertial Reference System
35
5. ADIRS
What are some of the parameters the Air Data Reference System provides?
Barometric altitude, Airspeed, Overspeed Warnings, Temperature, AOA, MACH.
36
5. ADIRS
What are some of the parameters the IR provides?
Attitude, FPV, Track, Heading, Acceleration, Angular Rates, GS and Aircraft Position.
37
5. ADIRS
If #1 IR fault light illuminated steady, what are some of the important ECAM procedures that you would expect to see?
IR 1...OFF
ATT/HDG to Capt 3 on EIS switching panel
38
5. ADIRS
If the AIR DATA portion of #1 ADIRU failed, what are some of the important ECAM procedures that you would expect to see?
#1 ADR pb...OFF
Air Data to Capt 3 on EIS switching panel
39
5. ADIRS
Explain the ADIRS Power-up and Initialization.
Switch OFF to NAV
ON BAT light illuminates and then extinguishes
White ALIGN light illuminates for the duration of alignment
40
5. ADIRS
What is the importance of observing the ON BAT light?
It tests the ADIRS ability to revert to battery power
41
5. ADIRS
What are some indications of an ADIR having reverted to battery power on the ground?
An external horn sounds
An ADIR and the blue AVNCS light illuminates on the External Power Panel.
42
5. ADIRS
What is the significance of a steady FAULT light on the IR?
IR has failed and cannot be recovered
43
5. ADIRS
What is the significance of a flashing FAULT light on the IR?
Navigation function is lost. Attitude and Heading may be recovered in ATT mode.
44
5. ADIRS
What could cause the flashing white ALIGN light to illuminate on the ground?
PPOS not entered within 10 minutes of alignment - within 3 minutes of fast-alignment
Large difference in LAT/LONG between shutdown position and entered position - 1 degree
Aircraft movement during alignment.
45
5. ADIRS
Can the ADR be turned OFF without losing the IR functions?
Yes
46
5. ADIRS
Can the IR be turned OFF without losing the ADR functions?
No
47
6. Overhead CB Panel
What is the significance of black and green CB’s?
Green monitored by ECAM
Black not monitored by ECAM
48
6. Overhead CB Panel
When would the AUDIO SWITCHING be used?
Enables Captain or FO to utilize the overhead Audio Control Panel in case of individual ACP failure
49
7. APU panel
What does the illumination APU MASTER SW FAULT indicate?
Automatic APU shutdown has occurred.
50
7. APU panel
What is the significance of the APU AVAIL light illumination?
APU is running above 99.5 % or 2 seconds after N speed reaching 95% (in practical terms it is ready to accept and support ELEC and/or AIR load)
51
7. APU panel
What condition in the APU system would cause an external horn to sound?
APU fire.
52
8. CABIN PRESS panel
What does selecting the MODE SEL from AUTO to MAN to AUTO accomplish?
Switches the active controller.
53
8. CABIN PRESS panel
How is the landing field elevation entered into the pressurization system in automatic, semi-automatic and manual modes?
Automatic = FMGC (LDG ELEV must be in AUTO)
Semi-automatic = by LDG ELEV selector button
Manual = By selecting the MODE SEL to MAN and then using the MAN V/S CTL toggle switch
54
8. CABIN PRESS panel
What does selecting the DITCHING push button to ON accomplish?
Closes the outflow valve
Closes the emergency RAM AIR inlet
Closes the Avionics Ventilation Inlet and Extract valves
Closes pack flow control valves
(closes all valves below the waterline)
55
9. ANTI-ICE panel
What is accomplished if the Wing Anti Ice push button is selected ON while the aircraft is on the ground?
The system will self-test for 30 seconds, then the valves will close until the aircraft is airborne.
56
9. ANTI-ICE panel
What does the WING FAULT light illumination on the ANTI ICE panel indicate?
Valve disagreement. (comes on momentarily when valve in transit)
Low pressure.
57
9. ANTI-ICE panel
What does the ENG 1(2) FAULT light illumination on the ANTI ICE panel indicate?
Valve disagreement. (comes on momentarily when valve in transit)
58
9. ANTI-ICE panel
Describe the PROBE/WINDOW HEAT Logic.
Probes and Window Heat come on automatically (Probes LOW on ground/HIGH airborne) with at least one engine running or aircraft airborne.
59
10. AIR COND panel
PACK FLOW is selected to LO, NORM or HIGH and only the APU is providing BLEED AIR or one pack is selected OFF, what will the Pack Flow Rate?
HIGH flow rate, since the flow rate function is automatic.
60
10. AIR COND panel
If the HOT AIR valve faults, what will happen to the temperature control system?
All trim air valves close and pack 1 controls the cockpit temperature to the last selected value – PACK 2 controls the cabin to the averages selected by the FWD and AFT CABIN temperature selector knobs.
61
10. AIR COND panel
How are the PACKS controlled and operated?
Electrically controlled and pneumatically operated.
62
10. AIR COND panel
What are some potential causes for a PACK FAULT light?
low air pressure
compressor outlet overheat
pack outlet overheat
63
10. AIR COND panel
What are SOME potential causes for ENG BLEED FAULT light
Bleed overpressure
Bleed overheat
Wing or engine leak on the related side
Bleed valve NOT closed during engine start
Bleed valve NOT closed with the APU BLEED on
64
10. AIR COND panel
XBLEED Valve
SHUT = the valve is closed.
AUTO = open if the APU bleed valve is open – closed if APU bleed valve is closed or there is a wing, pylon or APU leak (except during an engine start).
OPEN = the valve is open.
65
10. AIR COND panel
What does APU BLEED FAULT illumination indicate?
APU bleed leak.
66
10. AIR COND panel
What does selecting the RAM AIR push button accomplish?
Ram Air inlet opens if the differential pressure is less than 1 PSI.
67
11. ELEC panel
What is the minimum battery voltage?
25.6
68
11. ELEC panel
What would you do if BAT voltage is below 25.6?
With external power, select BAT pb’s to AUTO
69
11. ELEC panel
Explain how to conduct the BAT check.
Select ELEC on ECAM
BAT 1 & 2 OFF then on
Check BAT charge current is <60 amps and decreasing within 10 seconds
*What if it fails the test? Call MX
70
11. ELEC panel
Is this an AC airplane or DC airplane?
AC
71
11. ELEC panel
If all AC is lost, what happens?
DC power from the batteries is converted into AC
72
11. ELEC panel
The engine GEN FAULT light is illuminated before engine start. Is this normal?
Yes
73
11. ELEC panel
What is an IDG?
Integrated Drive Generator.
74
11. ELEC panel
How do you explain how an IDG works?
Takes variable engine output and gives a constant output.
75
11. ELEC panel
What is one precaution when disconnecting the IDG?
Don’t hold for longer than 3 seconds or you will damage the solenoid.
76
11. ELEC panel
Can the IDG be reconnected?
No. MX function
77
11. ELEC panel
Describe the function of the BUS TIE in AUTO?
Allows single source of power to run entire elec system
Allows connection of the APU GEN or EXT power to system
Inhibits multiple sources connected simultaneously
78
11. ELEC panel
If GEN 1 fails to supply AC Bus 1, what happens?
AC BUS 2 powers the system through the bus tie.
79
11. ELEC panel
How is the AC ESS bus normally powered?
From AC Bus 1
80
11. ELEC panel
If AC BUS 1 fails, how is the AC ESS bus powered?
AC Bus 2 automatically feed the AC ESS bus.
81
11. ELEC panel
What indication will you get on the ELEC panel that AC BUS 2 is feeding the AC ESS bus?
AC ESS FEED ALTN light on
82
11. ELEC panel
What does a GALLEY fault light indicate?
At least one generator load is above 100% rated output. (will all or main galleys shed)
83
11. ELEC panel
Explain the Auto function of the GALLEY pushbutton.
Sheds main galley if only 1 gen is avail in flight or
Sheds main galley if only 1 gen is avail on the ground
84
11. ELEC panel
How is the BATTERY BUS normally powered?
DC BUS 1 through the DC tie contactor
85
11. ELEC panel
How does the EMER Generator connect to the ELEC system?
Connects to the AC essential bus which powers the DC essential bus.
86
11. ELEC panel
What is the difference of the APU Gen Fault and the ENG fault?
Both are indicators of a line contactor open. The diff is the fault may also indicate a
Fault detected by the ENG GCU.
87
11. ELEC panel
What does a BAT fault light indicate?
Battery charging current outside limits. BAT contactor opens.
88
12. FUEL panel
Describe the layout of the fuel tanks in the A320.
Center tank, and wing tanks made up of inner, outer and vent tanks.
89
12. FUEL panel
Generally, what is the total fuel capacity?
42,000 lb (41, 285)
90
12. FUEL panel
Why is it possible for the fuel computer to indicate 42, 200 lbs on ECAM when fueled to MAX capacity?
The fuel can expand by 2% without venting overboard.
91
12. FUEL panel
Where are the fuel pumps located?
2 Center tank pumps and 2 wing tank pumps per wing.
The APU has it’s own pump. (When does it run? CTR tank pumps OFF)
92
12. FUEL panel
Are the pumps in the center tank different from the wing pumps?
They are identical pumps, but plumbing creates different outputs. The Center pumps have a greater system output
93
12. FUEL panel
Explain the flow of fuel from before engine start to taxi out. (Assume full tanks)
At engine start the fuel is fed from the wing tanks. After both engines are started, the center tank pumps turn on and continue to run until slats are selected then the stop. At t/o the engines feed fuel from the respective wing tanks. When slats are zero, the fuel is fed from the center tank. (After center tank runs dry, the pumps continue to run for 5 min)
94
12. FUEL panel
What does a fault light in one of the ENG fuel pumps indicate?
Low delivery pressure
95
12. FUEL panel
What does a fault light in the MODE selector indicate?
Failure of the AUTO mode
Center tank has more than 550lb and either wing tank has less than 11K
96
12. FUEL panel
How do you know that fueling is in progress?
REFUELING message on ECAM.
97
12. FUEL panel
Does this mean that fuel is entering the tanks?
NO. It means the refueling fuel door is open.
98
12. FUEL panel
Is fuel used to cool the IDG?
Yes.
99
12. FUEL panel
Where does this fuel return to?
Wing tanks.
100
12. FUEL panel
What if this return fuel fills the wing tanks with center tanks feeding?
The center tank pumps will cut off until the wing tank quantity is reduced by 1100lb.
101
13. HYD panel
How are the three HYD systems referred to as?
Green, Blue and Yellow Systems
102
13. HYD panel
How is each system powered?
Green - Engine Driven
Blue - Electrical
Yellow – Engine Driven and Electrical
103
13. HYD panel
When does the BLUE pump normally operate?
After the first engine is started
104
13. HYD panel
The RAT supplies the BLUE hydraulic system. Does the RAT deploy automatically with loss of BLUE pressure?
No. It must be deployed manually
105
13. HYD panel
What can be done to correct low ACUM PRESS indication?
On the ground, coordinate with personnel and turn on the Yellow ELEC pump
106
13. HYD panel
With no HYD system power, how can the forward CARGO door be opened?
By using a hand pump
107
13. HYD panel
What causes the PTU to operate in AUTO?
Differential pressure of 500 psi between Green and Yellow
After first engine start until second engine starts
108
13. HYD panel
What are some users of the Green system? QRM can be referenced.
Landing Gear
Normal Brakes
Slats and Flaps
#1 Thrust reverser
109
13. HYD panel
What are some users on the Blue system?
Emergency generator
Slats
110
13. HYD panel
What are some users of the Yellow system?
Flaps
NWS
Alternate brakes
111
13. HYD panel
What do the priority valves do in the HYD systems?
What do the priority valves do in the HYD systems?
112
13. HYD panel
What would cause a fault light in the ENG 1 pump?
Pump low pressure
Overtemp in reservoir
Low air pressure in res
Low quantity
113
13. HYD panel
How do you know which fault has occurred?
ECAM will display the fault
114
14. FIRE panel
Where are the engine fire loops installed?
Pylon nacelle
Engine core
Fan Section
115
14. FIRE panel
What happens if both fire loops fail simultaneously?
FIRE warning will be issued (If the failure occurs within 5 seconds)
116
14. FIRE panel
What does amber DISCH light mean?
Bottle has lost its pressure either by a fault or pilot selection
117
14. FIRE panel
How many fire bottles are provided for each engine?
Two
118
14. FIRE panel
What happens when the engine fire PB is pushed?
Silences the aural fire warning
Arms the squibs
Closes the hydraulic fire valve
Closes the LP fuel valve
Closes the engine fuel return valve
Deactivates the generator
Closes the pack flow control
Closes the engine bleed valves
119
14. FIRE panel
What happens when the ENG FIRE test button is pressed?
Continuous Repetitive Chime sounds
Master warning lights flash
ENG FIRE PB illuminates red
SQUIB and DISCH lights illuminate
ECAM fire warning
Fire light on ENG panel
120
14. FIRE panel
What should occur if the APU is operating and an APU fire is detected?
On the ground - APU auto shut down and bottle discharge
In the air – no automatic functions
121
15. VENTILATION panel
What are some potential causes for the illumination of the BLOWER FAULT light?
Low blower pressure
Duct overheat
Computer power supply failure
Smoke warning activated
122
15. VENTILATION panel
What are some potential causes for the illumination of the EXTRACT FAULT light?
Low extract pressure
Computer power supply failure
Smoke warning activated
123
15. VENTILATION panel
What condition in the avionics ventilation system would cause an external horn to sound?
BLOWER FAULT or EXTRACT FAULT illumination on the ground with both engines stopped.
124
15. VENTILATION panel
Describe the avionics ventilation system?
It is a fully automated system that considers the skin temperature and adjust inlet and outlet flaps to optimize cooling and air flow.
125
15. VENTILATION panel
NORMAL OPERATIONS
(during normal operations, the AIR COND INLET VALVE remains always closed)
126
15. VENTILATION panel
OPEN CIRCUIT CONFIGURATION
Both the inlet and the outlet flaps are fully open (ACFT is on ground; skin temperature above a set threshold)
127
15. VENTILATION panel
CLOSED CIRCUIT CONFIGURATION
Both the inlet and outlet flaps are fully closed. The SKIN EXCHANGE INLET BYPASS VALVE is open, allowing air to the cargo underfloor, eventually exiting via the outflow valve (ACFT is on the ground or in-flight; skin temperature below a set threshold).
128
15. VENTILATION panel
NORMAL INTERMEDIATE CIRCUIT CONFIGURATION
The inlet flap is fully closed, the outlet small flap is open (ACFT is in-flight; skin temperature is above a set threshold).
129
15. VENTILATION panel
ABNORMAL OPERATIONS
(during abnormal operations, the AIR COND INLET VALVE always opens providing fresh ventilation air)
130
15. VENTILATION panel
BLOWER or EXTRACT FAULT
Both inlet and outlet flaps fully closed, SKIN EXCHANGE INLET BYPASS VALVE closed.
131
15. VENTILATION panel
SMOKE CONFIGURATION
Once the BLOWER and EXTRACT push buttons have been selected to OVRD, the blower fan will stop, the extract fan will continue to run – the inlet flap closes, the small outlet flap opens the SKIN EXCHANGE ISOLATION VALVE closes and the SKIN EXCHANGE INLET BYPASS VALVE closes.
132
16. CARGO SMOKE panel
Describe the cargo smoke test.
Press to test for three seconds until the red SMOKE lights in the FWD and AFT push buttons illuminate – test sequence will run twice; Red SMOKE lights, CRC, DISCHARGE lights and ECAM warning.
133
16. CARGO SMOKE panel
Following a cargo smoke indication and consequent discharging of the cargo smoke bottle, what would be the expected indication on the CARGO SMOKE panel?
The SMOKE light and associated ECAM warning may remain illuminated due to the HALON concentration present in the cargo compartment.
134
16. CARGO SMOKE panel
How many fire extinguishing bottles are there in the cargo extinguishing system?
One that has ducting to both FWD and AFT compartments, but the discharge can only be directed to one compartment.
135
17. CARGO HEAT panel
What is the significance of the illumination of the HOT AIR FAULT light?
Duct overheat is detected.
136
17. CARGO HEAT panel
What is the significance of the illumination of the AFT ISOL VALVE FAULT light?
Either the inlet or the outlet valve is not in the selected position.
137
18. Glareshield
What are some causes for AUTOLAND light?
Excessive LOC or GS deviation or signal failure
Radio Altimeter difference of greater than 15 feet
Both autopilots fail
138
18. Glareshield
What should the pilot action be in case the AUTOLAND warning light illuminates below 200 feet RA?
Immediate Go-around.
139
18. Glareshield
Explain the side stick operation and the associated glare shield SIDE STICK PRIORITY light.
Normally only one side stick should be operated at any given time.
Should there be dual input, an aural “DUAL INPUT” will be annunciated over the speaker and the SIDE STICK PRIORITY green CAPT and F/O lights will flash - side stick inputs are algebraically summed.
Any time a pilot monitoring has to assume control, it MUST be verbally annunciated ( “I
HAVE CONTROL”) – the pilot taking over MUST press and hold the takeover push button.
If the pilot previously flying does not relinquish control or there is a malfunction present, the side stick can be rendered inoperative by holding the takeover push button for 40 seconds. An aural alert “PRIORITY LEFT (RIGHT”) will be annunciated over the speaker and the SIDE STICK PRIORITY red arrow light will illuminate in front of the pilot losing authority.
The pilot having lost side stick authority can regain it by momentarily pressing the takeover push button.
140
18. Glareshield
What should be selected on the EFIS panel during the Cockpit Preparation?
ARC or ROSE NAV (more than 70 degree turn after takeoff)
Minimum range to display the first fix, weather – in all cases less than 40 NM
Other selectors as appropriate
141
18. Glareshield
If a HDG is pre-selected (not pulled) to the FCU HDG window prior to takeoff, what lateral mode will be active after liftoff?
RWY TRACK
142
18. Glareshield
If MANAGED LATERAL DOT is displayed next to the FCU HDG window prior to takeoff, what lateral mode will be active after liftoff?
NAV
143
19. Center Pedestal
Describe the preflight actions on ECAM CONTROL PANEL
Check HYD - quantity, ENG – oil Quantity, DOORS – OXY quantity
144
19. Center Pedestal
Should the ECAM CONTROL PANEL fail, what functions are available as hard-wired buttons?
CLR, RCL, STS, EMER CANC and ALL
145
19. Center Pedestal
What does the EMER CANC accomplish?
Cancels the audio for warning messages (without removing any ECAM message)
Cancels the present caution for the rest of the flight – calls up the STATUS page, which displays “CANCELLED CAUTION” and the TITLE of the failure
Inhibited message can be recalled by holding RCL for more than three seconds
146
19. Center Pedestal
What is the purpose of having the EMER CANC pushbutton?
Used to cancel spurious MASTER CAUTIONS
147
19. Center Pedestal
If a Radio Management Panel 1 (RMP 1) fails, how can VHF 1 still be used?
By using RMP 2 or 3
148
19. Center Pedestal
How is AUTOTHRUST normally armed?
By advancing the thrust levers to TOGA or FLX
149
19. Center Pedestal
What would be the normal FMA indications during a takeoff roll with FLX thrust and proper temperature set on a RWY with a localizer?
MAN FLX, SRS, RWY, A/THRUST (blue)
150
19. Center Pedestal
What would the FMA indications be during a takeoff roll with THRUST LEVERS were in TOGA?
MAN TOGA, SRS, RWY, A/THRUST (blue)
151
19. Center Pedestal
How should AUTOTHRUST be turned off?
Match the blue TLA indicators to the present thrust setting and push the IDP’s or move THRUST LEVERS to IDLE
152
19. Center Pedestal
What should the pilot do to get out of TOGA LOCK?
Move the THRUST LEVERS one notch and push the IDP’s or move THRUST LEVERS to IDLE
153
19. Center Pedestal
What should the pilot do to get out of THRUST LOCK?
Move the thrust levers – ECAM will annunciate this as well
154
19. Center Pedestal
AUTOTHRUST active zone for 2-engine operations?
From slightly above IDLE to CLB
155
19. Center Pedestal
AUTOTHRUST active zone for OEI operations?
From slightly above IDLE to MCT
156
19. Center Pedestal
When selecting flap lever to 1 after the flaps have been at CONF 2 or higher, what setting will the flaps/slats go to?
CONFIGURATION 1 + F
Maximum speed 215 KT with automatic retraction of flaps when passing 210 KT
157
19. Center Pedestal
What is the normal flap setting for a go-around?
One setting up from the approach flap setting
If the approach was made at CONF 3 in high density altitude and at high landing weight (QRH 2.43), the flaps are selected from CONF 3 directly to CONF 1
