問題一覧
1
Automatically when overflying the DECEL pseudo waypoint with NAV, LOC* or LOC engaged. It can also be manually activated by selecting ACTIVATE PHASE on the PERF page
2
When HDG or TRK lateral guidance modes are engaged, select the ACTIVATE SECONDARY prompt on the SEC INDEX page of the MCDU. This prompt will not be available in NAV unless the active leg in the primary and secondary are the same
3
At the next refueling operation
4
V2+10 all engines operating, if OEl the highest of V2 or the airspeed at the time of engine failure (maximum V2+15 knots)
5
Wing anti-ice valves close, engine anti-ice valves close
6
When using APU bleed or during single pack operation
7
The AUDIO SWITCHING selector should be set to CAPT/3, this connects the Captain's headset to ACP3 on the overhead panel
8
WTBs
9
CAB
10
TAT (Total Air Temperature)
11
Armed FMA modes are displayed in blue (selected) or magenta (managed)
12
Flight management and flight guidance
13
DMC 1, 2, or 3 depending on the configuration of the ATT HDG and AIR DATA rotary selectors on the switching panel
14
Packs, re-circulated cabin air, emergency ram air inlet, and LP ground connector
15
A 15 minute cooling period is required following 4 failed start cycles
16
The word SLIDE appears in WHITE next to the associated door
17
16,000 ft
18
A steady FAULT light indicates that the NAV mode of the associated IR has been lost. Refer to the ECAM procedure to check If it is possible to recover aetude and heading in ATT mode
19
Normal operation of a system used temporarily
20
Load factor limitation is the only protection available in alternate law. High speed and low speed stabilities may be available
21
Normal system operation
22
The ADR or IR part of an ADIRU can be individually switched OFF using the IR or ADR pushbuttons. Setting the IR Mode Selector to OFF will remove power from the whole ADIRU
23
Position 1 turns on the logo lights and the first set of navigation lights, position 2 turns on the logo lights and the second set of navigation lights
24
In the pylon nacelle, in the engine core, and in the engine fan section
25
The corresponding surfaces operate at half speed
26
A fire warning is triggered if a break occurs in both fire detection loops within 5 sec of each other (flame effect)
27
One LGCIU controls one complete gear cycle, then switches over automatically to the other LGIU at the completion of the retraction cycle. It also switches over in the case of failure
28
120% of normal
29
The weather radar
30
RMP 1
31
The command for ground spoiler deployment from the SECs (wheel speed > 72 kt) will activate the autobrake
32
The pressure in the oxygen bottle is less than 1500PSI. Refer to the limitations section of the FCOM to determine whether the remaining quantity is not below the minimum for the number of occupants in the flight deck
33
LP and HP fuel shutoff valves
34
The avionics ventilation system extracts air from the cockpit panels and avionics compartment, and then removes heat using a skin air heat exchanger
35
Initially load factor transitioning to an angle of attack demand. If the side stick is later released the F/CTRL computers will maintain an AoA equal to alpha prot, until the sidestick is pushed forward
36
Normally closed
37
Ailerons and spoilers 2, 3, 4 and 5
38
PA announcements to the cabin only
39
FWC
40
On the WHEEL SD page, at least one green triangle for each landing gear strut is sufficient to confirm that the landing gear is down-locked. Even if a red UNLK light is illuminated on the landing gear indicator panel
41
FMGC 2
42
It engages <400 ft RA until approximately 40RA when it is replaced by FLARE. It can be disengaged by setting TOGA thrust, or by disconnecting both AP and FD
43
Push the APP pushbutton on the FCU. The ILS information (including LOC and G/S scales) will not be displayed on the PFD unless the LS push button is selected on the EFIS panels
44
Radome, nose gear bay, main gear bay, air conditioning compartment, and the tail cone
45
3 phase AC 115/200v 400Hz, and 28v DC
46
The FADEC automatically closes the start valve and cuts off ignition when N2 reaches 50%
47
The WHEEL page appears on the LOWER ECAM DU
48
Above 33° an input on the sidestick will be required to hold the bank attitude. Full deflection will give a roll rate of 15% and the bank angle will not exceed 67°
49
7:2 x ELACS, 3 x SECs, 2 x FACS
50
Yes, provided the x-bleed is selected open, one pack is selected off and the fire push button has not been pushed
51
Closed
52
Mechanical backup allows the flight crew to manage a temporary loss of 5 flight control computers. The THS and rudder are mechanically controlled, and hydraulically actuated. MAN PITCH TRIM ONLY (RED) is displayed on the PFD
53
LP and HP fuel shutoff valves
54
2 channels: 1 SLAT and 1 FLAP
55
All ECAM cautions and warnings, aural warnings, master caution and master warning lights are lost
56
3000 PSI (2500 PSI when powered by the RAT)
57
The door unlocks automatically, but remains closed
58
IDG 90 KVA, APU 90 KVA, emergency generator 5 KVA, Static Inverter 1 KVA
59
8.6 PSI
60
280 kt
61
215 kt
62
38 kt (gusts included)
63
70 kt
64
Clean - 1g to 2.5g. Other configurations 0g to 2g
65
± 2%
66
230 kt
67
+9 to -1 PSI
68
220 kt
69
1,500 kg
70
20,000 ft
71
350/0.82
72
65 kt
73
10 min during single engine operations
74
177 kt
75
1.15
76
The entire length available
77
Green dot speed
78
Maximum of 10 min
79
5, 10
80
Includes VREF + VREF+APPR COR
81
99
82
Aircraft weight and environmental conditions
83
3 mm
84
25%
85
All of the answers are correct
86
Lowest of certified limit takeoff weight and performance limit takeoff weight
87
2.5
88
Vis at CONF FULL
89
Runway length, Obstacles, Tire Speed
90
Final Approach Speed (VAPP) when a system failure affects the landing performance
91
V1 is the adjusted lowest safe go speed
92
-1
93
-5
94
14
95
On the fuselage side beneath the right wing
96
19,185 kg
97
Yes, when electrical power is not available, the operator can use a hydraulic hand pump to operate the cargo doors
98
Wing tanks
99
On the upper surface of each wing
100
If it is not possible to reach the passenger cabin, evacuate via a sliding window, using an escape rope
CPL HUMAN PERFORMANCE AND LIMITATIONS (1)
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97問 • 1年前問題一覧
1
Automatically when overflying the DECEL pseudo waypoint with NAV, LOC* or LOC engaged. It can also be manually activated by selecting ACTIVATE PHASE on the PERF page
2
When HDG or TRK lateral guidance modes are engaged, select the ACTIVATE SECONDARY prompt on the SEC INDEX page of the MCDU. This prompt will not be available in NAV unless the active leg in the primary and secondary are the same
3
At the next refueling operation
4
V2+10 all engines operating, if OEl the highest of V2 or the airspeed at the time of engine failure (maximum V2+15 knots)
5
Wing anti-ice valves close, engine anti-ice valves close
6
When using APU bleed or during single pack operation
7
The AUDIO SWITCHING selector should be set to CAPT/3, this connects the Captain's headset to ACP3 on the overhead panel
8
WTBs
9
CAB
10
TAT (Total Air Temperature)
11
Armed FMA modes are displayed in blue (selected) or magenta (managed)
12
Flight management and flight guidance
13
DMC 1, 2, or 3 depending on the configuration of the ATT HDG and AIR DATA rotary selectors on the switching panel
14
Packs, re-circulated cabin air, emergency ram air inlet, and LP ground connector
15
A 15 minute cooling period is required following 4 failed start cycles
16
The word SLIDE appears in WHITE next to the associated door
17
16,000 ft
18
A steady FAULT light indicates that the NAV mode of the associated IR has been lost. Refer to the ECAM procedure to check If it is possible to recover aetude and heading in ATT mode
19
Normal operation of a system used temporarily
20
Load factor limitation is the only protection available in alternate law. High speed and low speed stabilities may be available
21
Normal system operation
22
The ADR or IR part of an ADIRU can be individually switched OFF using the IR or ADR pushbuttons. Setting the IR Mode Selector to OFF will remove power from the whole ADIRU
23
Position 1 turns on the logo lights and the first set of navigation lights, position 2 turns on the logo lights and the second set of navigation lights
24
In the pylon nacelle, in the engine core, and in the engine fan section
25
The corresponding surfaces operate at half speed
26
A fire warning is triggered if a break occurs in both fire detection loops within 5 sec of each other (flame effect)
27
One LGCIU controls one complete gear cycle, then switches over automatically to the other LGIU at the completion of the retraction cycle. It also switches over in the case of failure
28
120% of normal
29
The weather radar
30
RMP 1
31
The command for ground spoiler deployment from the SECs (wheel speed > 72 kt) will activate the autobrake
32
The pressure in the oxygen bottle is less than 1500PSI. Refer to the limitations section of the FCOM to determine whether the remaining quantity is not below the minimum for the number of occupants in the flight deck
33
LP and HP fuel shutoff valves
34
The avionics ventilation system extracts air from the cockpit panels and avionics compartment, and then removes heat using a skin air heat exchanger
35
Initially load factor transitioning to an angle of attack demand. If the side stick is later released the F/CTRL computers will maintain an AoA equal to alpha prot, until the sidestick is pushed forward
36
Normally closed
37
Ailerons and spoilers 2, 3, 4 and 5
38
PA announcements to the cabin only
39
FWC
40
On the WHEEL SD page, at least one green triangle for each landing gear strut is sufficient to confirm that the landing gear is down-locked. Even if a red UNLK light is illuminated on the landing gear indicator panel
41
FMGC 2
42
It engages <400 ft RA until approximately 40RA when it is replaced by FLARE. It can be disengaged by setting TOGA thrust, or by disconnecting both AP and FD
43
Push the APP pushbutton on the FCU. The ILS information (including LOC and G/S scales) will not be displayed on the PFD unless the LS push button is selected on the EFIS panels
44
Radome, nose gear bay, main gear bay, air conditioning compartment, and the tail cone
45
3 phase AC 115/200v 400Hz, and 28v DC
46
The FADEC automatically closes the start valve and cuts off ignition when N2 reaches 50%
47
The WHEEL page appears on the LOWER ECAM DU
48
Above 33° an input on the sidestick will be required to hold the bank attitude. Full deflection will give a roll rate of 15% and the bank angle will not exceed 67°
49
7:2 x ELACS, 3 x SECs, 2 x FACS
50
Yes, provided the x-bleed is selected open, one pack is selected off and the fire push button has not been pushed
51
Closed
52
Mechanical backup allows the flight crew to manage a temporary loss of 5 flight control computers. The THS and rudder are mechanically controlled, and hydraulically actuated. MAN PITCH TRIM ONLY (RED) is displayed on the PFD
53
LP and HP fuel shutoff valves
54
2 channels: 1 SLAT and 1 FLAP
55
All ECAM cautions and warnings, aural warnings, master caution and master warning lights are lost
56
3000 PSI (2500 PSI when powered by the RAT)
57
The door unlocks automatically, but remains closed
58
IDG 90 KVA, APU 90 KVA, emergency generator 5 KVA, Static Inverter 1 KVA
59
8.6 PSI
60
280 kt
61
215 kt
62
38 kt (gusts included)
63
70 kt
64
Clean - 1g to 2.5g. Other configurations 0g to 2g
65
± 2%
66
230 kt
67
+9 to -1 PSI
68
220 kt
69
1,500 kg
70
20,000 ft
71
350/0.82
72
65 kt
73
10 min during single engine operations
74
177 kt
75
1.15
76
The entire length available
77
Green dot speed
78
Maximum of 10 min
79
5, 10
80
Includes VREF + VREF+APPR COR
81
99
82
Aircraft weight and environmental conditions
83
3 mm
84
25%
85
All of the answers are correct
86
Lowest of certified limit takeoff weight and performance limit takeoff weight
87
2.5
88
Vis at CONF FULL
89
Runway length, Obstacles, Tire Speed
90
Final Approach Speed (VAPP) when a system failure affects the landing performance
91
V1 is the adjusted lowest safe go speed
92
-1
93
-5
94
14
95
On the fuselage side beneath the right wing
96
19,185 kg
97
Yes, when electrical power is not available, the operator can use a hydraulic hand pump to operate the cargo doors
98
Wing tanks
99
On the upper surface of each wing
100
If it is not possible to reach the passenger cabin, evacuate via a sliding window, using an escape rope