問題一覧
1
Saving in space and weight
2
The rate of charging was too high
3
Motor over to prevent torching when re starting
4
Initially increase, then decrease
5
Cabin differential pressure reaches a pre set value
6
The outflow valve
7
Pressure maintaining valve
8
SG decreases with temperature rise
9
At high altitudes at all times
10
Is is almost incompressible
11
Pneumatics do not require return lines but hydraulic systems do
12
Increase in lift and drag coefficients, and a nose up pitch moment
13
Improved boundary layer airflow over flaps
14
When an unsafe radio height is reached, with the aircraft NOT in the landing configuration
15
Mechanically, when the aircraft is on the ground
16
By a governor
17
Selector valve
18
The bus tie breaker switch
19
Lower propulsive efficiencies at high subsonic mach numbers
20
Monitors only autopilot and autopilot support system integrity
21
It could be high or low speed buffet, as it is difficult to tell at high altitude
22
Curved surfaces in various parts of the aircraft accelerate the air to greater than free stream mach number
23
Servo tab
24
Ensure the tank walls do NOT rupture when in turbulence or during manoeuvres
25
To prevent the fluid from foaming due to low ambient pressures at high altitudes
26
Both TA's and RA's are inhibited by GPWS warnings
27
The system is armed to capture the glideslope and altitude hold will automatically cancel when this occurs
28
The speed/load factor limits within which the aircraft is to be operated
29
On aircraft that do not have triple hydraulic system redundancy
30
The rearward movement of the centre of pressure and reduced tailplane down load
31
Require a lower than normal attitude, and a higher airspeed on approach
32
Increases
33
The primary function of ground spoilers is to reduce lift and increase braking effectiveness
34
Decrease than increase
35
Reduce the landing and takeoff speeds and distances needed
36
Stall warning and flap fatigue life may be compromised
37
Low, and high speed stall buffet speed IAS values become closer together
38
Light elevator control forces and decreased pitch stability
39
Greater elevator force is required to change the pitch attitude than with an aft CoG
40
Both IAS and EAS values increase, EAS will always be equal to or less than IAS value
41
When the bi metalic strips have cooled
42
Relevant at takeoff weight only
43
Increase
44
Bank and rudder are used in coordination to counteract the yaw produced by the live engine
45
Reduces trailing edge flap effectiveness
46
Inboard flaps
47
2
48
Cautions are automatically inhibited from 80kts to 400ft RA or 20 seconds after lift off, whichever occurs first
49
Tyre Size
50
The upper end of the rpm range
ATPL Systems
ATPL Systems
Will Erwin · 50問 · 1年前ATPL Systems
ATPL Systems
50問 • 1年前ATPL Systems II
ATPL Systems II
Will Erwin · 50問 · 1年前ATPL Systems II
ATPL Systems II
50問 • 1年前ATPL Systems III
ATPL Systems III
Will Erwin · 50問 · 1年前ATPL Systems III
ATPL Systems III
50問 • 1年前ATPL Systems IV
ATPL Systems IV
Will Erwin · 50問 · 1年前ATPL Systems IV
ATPL Systems IV
50問 • 1年前Avery Systems I
Avery Systems I
Will Erwin · 50問 · 1年前Avery Systems I
Avery Systems I
50問 • 1年前Avery Systems Test II
Avery Systems Test II
Will Erwin · 50問 · 1年前Avery Systems Test II
Avery Systems Test II
50問 • 1年前Avery Test III
Avery Test III
Will Erwin · 50問 · 1年前Avery Test III
Avery Test III
50問 • 1年前Avery Test IV
Avery Test IV
Will Erwin · 50問 · 1年前Avery Test IV
Avery Test IV
50問 • 1年前ATPL Met Revision I
ATPL Met Revision I
Will Erwin · 11問 · 1年前ATPL Met Revision I
ATPL Met Revision I
11問 • 1年前ATPL Met Revision 2
ATPL Met Revision 2
Will Erwin · 10問 · 1年前ATPL Met Revision 2
ATPL Met Revision 2
10問 • 1年前ATPL Met Revision 3
ATPL Met Revision 3
Will Erwin · 10問 · 1年前ATPL Met Revision 3
ATPL Met Revision 3
10問 • 1年前ATPL Met Revision 4
ATPL Met Revision 4
Will Erwin · 12問 · 1年前ATPL Met Revision 4
ATPL Met Revision 4
12問 • 1年前ATPL Met Revision 5
ATPL Met Revision 5
Will Erwin · 12問 · 1年前ATPL Met Revision 5
ATPL Met Revision 5
12問 • 1年前ATPL Met Revision 6
ATPL Met Revision 6
Will Erwin · 11問 · 1年前ATPL Met Revision 6
ATPL Met Revision 6
11問 • 1年前ATPL Met Revision 7
ATPL Met Revision 7
Will Erwin · 12問 · 1年前ATPL Met Revision 7
ATPL Met Revision 7
12問 • 1年前ATPL Met Revision 8
ATPL Met Revision 8
Will Erwin · 11問 · 1年前ATPL Met Revision 8
ATPL Met Revision 8
11問 • 1年前ATPL Met Revision 9
ATPL Met Revision 9
Will Erwin · 12問 · 1年前ATPL Met Revision 9
ATPL Met Revision 9
12問 • 1年前Wind, Cloud and Thunderstorm Test
Wind, Cloud and Thunderstorm Test
Will Erwin · 34問 · 1年前Wind, Cloud and Thunderstorm Test
Wind, Cloud and Thunderstorm Test
34問 • 1年前問題一覧
1
Saving in space and weight
2
The rate of charging was too high
3
Motor over to prevent torching when re starting
4
Initially increase, then decrease
5
Cabin differential pressure reaches a pre set value
6
The outflow valve
7
Pressure maintaining valve
8
SG decreases with temperature rise
9
At high altitudes at all times
10
Is is almost incompressible
11
Pneumatics do not require return lines but hydraulic systems do
12
Increase in lift and drag coefficients, and a nose up pitch moment
13
Improved boundary layer airflow over flaps
14
When an unsafe radio height is reached, with the aircraft NOT in the landing configuration
15
Mechanically, when the aircraft is on the ground
16
By a governor
17
Selector valve
18
The bus tie breaker switch
19
Lower propulsive efficiencies at high subsonic mach numbers
20
Monitors only autopilot and autopilot support system integrity
21
It could be high or low speed buffet, as it is difficult to tell at high altitude
22
Curved surfaces in various parts of the aircraft accelerate the air to greater than free stream mach number
23
Servo tab
24
Ensure the tank walls do NOT rupture when in turbulence or during manoeuvres
25
To prevent the fluid from foaming due to low ambient pressures at high altitudes
26
Both TA's and RA's are inhibited by GPWS warnings
27
The system is armed to capture the glideslope and altitude hold will automatically cancel when this occurs
28
The speed/load factor limits within which the aircraft is to be operated
29
On aircraft that do not have triple hydraulic system redundancy
30
The rearward movement of the centre of pressure and reduced tailplane down load
31
Require a lower than normal attitude, and a higher airspeed on approach
32
Increases
33
The primary function of ground spoilers is to reduce lift and increase braking effectiveness
34
Decrease than increase
35
Reduce the landing and takeoff speeds and distances needed
36
Stall warning and flap fatigue life may be compromised
37
Low, and high speed stall buffet speed IAS values become closer together
38
Light elevator control forces and decreased pitch stability
39
Greater elevator force is required to change the pitch attitude than with an aft CoG
40
Both IAS and EAS values increase, EAS will always be equal to or less than IAS value
41
When the bi metalic strips have cooled
42
Relevant at takeoff weight only
43
Increase
44
Bank and rudder are used in coordination to counteract the yaw produced by the live engine
45
Reduces trailing edge flap effectiveness
46
Inboard flaps
47
2
48
Cautions are automatically inhibited from 80kts to 400ft RA or 20 seconds after lift off, whichever occurs first
49
Tyre Size
50
The upper end of the rpm range