Auto Flight Q’s Flashcards
(387 cards)
1
Q
3 AP computers are considered
A
fail operable
2
Q
versine signal is proportional to
A
1 - cos(bank angle)
3
Q
the signal responsible for returning an aileron to its neutral position when an aircraft has reached its correct attitude as demanded by the AP is the
A
position feedback
4
Q
with glide slope armed the control of the pitch channel can
A
only be by the engaged mode when deviated from the beam
5
Q
heavy damping of dynamic stability will produce
A
a dynamically stable condition
6
Q
a rate gyro senses disturbances in
A
1axis
7
Q
the signal to the pitch channel of an autopilot during a turn is obtained from the
A
versine generator
8
Q
GO around is initiated
A
only by pressing the GA throttle switch
9
Q
an autopiot disconnect is indicated by
A
red light
10
Q
in a triplex autoland system, loss of a nav receiver prior to caputure of the localiser results in
A
reverting to a CAT 2 approach
11
Q
an autopilot slip-skid sensor signal goes primarily to the
A
rudder channel
12
Q
with an aircraft in a 90 degree banked turn holding the longitudinal axis of the aircraft level
A
altitude cannot be maintained
13
Q
IAS hold mode can only be engaged with altitude hold
A
disengaged
14
Q
autopilot disengage switch is positioned on the
A
side of the control wheel farthest from the throttle levers
15
Q
an aural warning in an autopilot system will sound when
A
autopilot is disengaged
16
Q
what radio equipment can be used in an AFCS
A
VOR, ILS
17
Q
when TURB is selected on the AP MCP
A
command signal is reduced 50% and manual modes only are available
18
Q
the pitch attitude of an aircraft with autopilot engaged can be changed by the
A
pitch switch CWS altitude hold IAS hold
19
Q
bank angle limiting applies restrictions to limit the angle of bank applied by limiting the
A
bank angle using the signal from the MCP selected bank angle
20
Q
A category 2 landing RVR is
A
400m
21
Q
profile or VNAV mode can be coupled to AT
A
if the flight director or AP is engaged
22
Q
after VOR capture on a ground check aileron movement will depend upon
A
course select error radio deviation and bank angle
23
Q
over amplification of the rate feedback signal will result in
A
sluggish operation of the servo
24
Q
if the AP automatically disconnects during autoland the audible warning
A
is switched off by the operation of the autopilot disengage switches
25
the loss of the vertical gyro signal to an FD system would cause
aircraft to overbank
26
SAS
opposes the helicopters inherent instability
27
the requirement of the position feedback signal is to
provide a signal proportional to the input signal angular displacement
28
an electro-mechanical servo is powered
electrically
29
the signals too the rudder channel for a coordination turn are
computed yaw rate and derived yaw rate
30
the airspeed lock
controls the pitch attuned of the aircraft
31
a CAT 3B aircraft using fail operational automatic landing equipment with fail operational control and roll out guidance will have
no decision height
32
what are the AP inputs for VOR capture mode
nav receiver output
33
the effect of loss of washout on LOC with cross wind is that aircraft will
fly parallel to the track
34
in an triple autoland system separate power supplies are required to make the system
fail operational
35
for an AP system certified to.a DH of 50ft (15m) or greater requirements include
fail-passive autoland systeem
36
after localiser capture washout of the standing error signal is carried out on
course select error
37
in an AFCS which of the following does not control through the AP channel
touch control steering
38
ground roll guidance by the rudder is effective to about
80k ground speed
39
when using a rate gyro to detect pitch attitude change the gimbal ring axis is
vertical or longitudinal
40
automatic ground roll control primary signal is
localiser signal
41
minimum operating speed for the auto throttle system is derived from
AOA
42
the purpose of the auto throttle clutch is to
allow the pilot to override the autothrotle system
43
the sense of a control surface position feedback signal will
oppose the signal causing the displacement of the control surface
44
the output of a slvaed directional gyro ti an autopilot consists of
azimuth angle
45
the electrical signal from a dynamic vertical sensor during a coordinated turn will
be zero
46
if a localiser signal only is fed to the roll channel of an aircraft towards the outer limit of the beam the aircraft will
fly in a circle
47
if a constant rate signal is fed to a rate-rate servo the servomotor will
run at a constant speed
48
in a helicopter control channel the force gradient spring cylinder
provides a zero datum about which control movements occur
49
the glideslope receiver gives an output to the autopilot in
pitch only
50
modulation consists of converting
DC to phase sensitive AC
51
compatible autopilot modes are
alt hold and VOR
52
LOC freq command
yaw and roll channels
53
when the AFCS is operating in the LOC mode the yaw damper is supplied with signals from
aileron control channel through a cross feed circuit
54
a heading error signal is generated by the difference between
aircraft heading and datum
55
prior to engagement with AP power on the trim indicators will indicate
standing voltage on the servo control loop
56
a CAT 2 facility performance ILS has an intersect height of
15m
57
the signal from a VG is used in an AP to give an output which is proportional to angle of disturbance
angle of distrubance
58
with alt hold mode engaged a pitch error signal will reduce
to zero over a period of time
59
during autoland the system is programmed to leave the glideslope at
the start of the flare phase a rat
60
e/rate system the servomotor speed is
proportional to the rate at which the disturbance takes place
61
operation of the AP trim controller
moves the trim tabs
62
in the AFCS when two channels are engaged in roll if a handover in one actuator occurs what indications will show
one API shows a hardover in direction while the other API shows a hardcover in the other direction
63
in a steady coordinated turn the heading signal to the autopilot is
opposed by the VG Signal
64
the purpose of duplex servo motor is to
prevent hardover or runaway
65
a series actuator has
limited authority eg 10%
66
on an AP ground check loss of servo motor rate feedback will
cause the control to oscillate about its datum
67
what is the main purpose of a servo in an autopilot system
move the control surface as commanded
68
with the AP in disconnect mode in a coordinated turn the
pilot operates the controls freely
69
after an automatic landing reverse thrust is applied
only if reverse thrust is manually selected
70
a course washout us used for
crosswind
71
an automatic landing system is fail operational if in the event of a failure
the landing can be completed automatically
72
marker beacon signals are used by the AFCS to sense the
distance from the runway
73
a two speed horizontal stab servomotor operates on high speed
when flaps are not retracted
74
signals used during the flare phase are
rad alt and integrated pitch
75
in a displacement AP system the position feedback
totally opposes the demand when the control surface is at the demand position
76
an AP turn control primarily controls
ailerons
77
the term model reference in an AFCS refers to
gain programming
78
the minimum reliability value for an autoland system is
1 in 10 power 7
79
in a pitch mode the VG signal will
oppose servo signal
80
the circuit used for washout is a
integrator
81
the speed of operation of a series actuator compared to a parallel actuator is
faster
82
a manometric airspeed lock will require
pitot and static pressure
83
a fail operational autopilot system will ensure that
the aircraft will continue its automatic landing in the event of a single failure
84
in a coordinated turn
the pilot operates the controls freely
85
during an autoland approach after localiser capture if the pilot presses the instinctive disconnect button
there is no aural warning
86
in an autopilot an integrator could be used to
prevent the aircraft from standing off a radio beam
87
version can be generated using a
resolver
88
the correct seq in autoland is
LOC, G/S attitude hold, Flare
89
during the autopilot reengagement the synchronisation circuits ensure that the
autopilot control circuits are at zero demand conditions prior to engagement
90
the two parameters which are used for an autoland category classification are
DH and RVR
91
on approach the aircrew operates the instinctive control wheel AP disconnect switch this results in
aural and visual warnings
92
an AP three-axis rate transmitter produces signals proportional to
yaw rate pitch rate and roll rate
93
in an AFCS system using auto trim movement of the pitch switch
will move both the control column and trim wheels
94
with fail operational AP the electrical power supplies are
isolated
95
when VOR/LOC mode is engaged a helicopter is controlled in the
roll axis onyl
96
the pilot cannot use the AP to control the aircraft with
TCS
97
successful synchronisation would be displayed by the trim indicator showing
zero
98
the pitch signal on a glide slope capture
increases
99
a failure during automatic landing with a fail passive system results in
system disconnect and the approach must be flown manually
100
during the landing phase with AT engaged when does the system enter THR CLP
at G/S capture
101
bank angle limiting concerns
maximum aircraft angle of bank that the AP can demand
102
when operating in turbulence mode
the gain of the control channels is decreased
103
when entering a banked turn to the right under autopilot control the aileron to rudder crossed will apply
right rudder
104
if GA is initiated during autoland the aircraft will
pitch nose up and increase speed
105
a voter system is used to ensure that
in multiplex systems a faulty channel is automatically disengaged
106
what signal may be added at touchdown
nose-down bias
107
during a ground check the vertical gyro is tilted in roll the versine signal will
give up elevator
108
an autopilot three-axis trim indicator shows out of trim condition by sensing
primary servomotor loads
109
in the approach mode and after glideslope capture the altitude hold facility
is inop because the signals from altitude hold are automatically switched out when the beam is captured
110
the flare phase of an autoland approach is controlled by the signals from
rad alt
111
in a typical AFCS the units consist of
VG DG amplifier
112
loss of rate feedback signal results in
oscillation of the control surface
113
trim indications are actuated by
DC milliammeters
114
on an autopilot ground check loss of control surface position feedback will cause the
control surface to move to its maximum position
115
a helicopter autopilot uses
rad alt for height hold and barometric altitude for altitude hold
116
two main AT control modes are engine thrust and
speed
117
an autopilot using a vertical gyro will automatically disengage with
loss of VG signal
118
an auto trim system controls the aircraft about the
lateral axis
119
what controls are used in response to the PVD display
nose wheel steering or rudder pedals
120
during autoland if one channel of a multichannel system detects an error between a control command signal and the control surface response all channels will disconnect if it Is a
duplex system
121
the term positive feedback refers to signals which are
of the same sense as the demand signal
122
the autopilot may capture a new altitude with
IAS or VS speed lock engaged
123
active stability
may be used in conjunction with a passively stable aircraft
124
when the clutch is energised the servomotor
connected to the control surface
125
electrically operated torque limiting is achieved by a resistor connected in
series with the control phase
126
when operated any torque pedal micro switches will
disengage heading hold
127
a position servo tachogenerator feedback signal is required to
damp out oscillations of a control movement
128
when reverse thrust is selected
AT disconnects
129
mach lock mode can be operated with
altitude hold mode disengaged
130
a versine signal is generated when the aircraft is
rolling
131
dutch roll is an oscillatory motion about the
yaw and roll axis
132
go around mode can be initiated
at and time after auto approach has been engaged
133
on an autopilot check loss of control surface psioiton feedback will cause
the control surface to move to its maximum position
134
a servomechanism having a tachogenerator only as a feedback device will
vary its speed with the input error voltage
135
a compatible mode in turbulence penetration is
heading
136
for an aircraft to be certified for a cat 2 autoland an AT system is
dependent on flight crew work load
137
in a helicopter AP
barometric capsules control altitude hold rad alt controls height hold
138
a servo motor has torque limiting for the purpose of limiting the
AP authority
139
in a yaw channel with heading hold the yaw synchroniser circuit operates when the
pilot puts his feet on the pedals
140
a radio coupled approach is
loc first followed by the glide slope
141
when a helicopter has AP engaged in alt hold and during the low speed regime range what used to maintain the altitude
longitudinal control
142
a radio coupled AP in pitch uses
glideslope
143
a rate servo tachogenerator feedback signal is required to
ensure proportional control movement for a given command signal
144
a triplex system loses one channel
pilot can continue with autoland
145
a triplex system loses one channel the system becomes a duplex system
duplex system
146
a triplex system loses one channel the system is now
fail passive
147
a yaw damper adds to its signal chain aileron and spoiler inputs
to help counteract adverse yaw
148
a yaw damper gain
decreases with speed
149
aileron signal is fed to the rudder channel
for turn coordination
150
aileron to rudder crossfeed is applied in autopilot system to
prevent aircraft yawing in the opposite direction to the turn
151
airspeed hold is a
pitch mode
152
alert height is when
a decision of whether to land is made
153
alpha range is applicable to
auto throttle
154
altitude hold mode what signal is washed out
pitch angle
155
altitude hold when engaged provides a washout input to the
autopilot pitch servo
156
an AC tachogenerator stator has
two windings 90d apart
157
an aircraft lands in autoland after touch down and thrust reversers are deployed what happens to auto throttle
automatically switches off
158
an aircraft will capture the autoland system at
1500ft
159
an autoland failure monitoring system must ensure that
the aircraft will continue its automatic landing in the event of single failure
160
an autoland is carried out in which sequence
LOC GS alt hold flare
161
an autoland system displays land 2 another failure will make the system
simplex
162
an automatic disengagement of an autopilot will cause
a red warning light to illuminate and an aural warning
163
an AFCS receives input from the following ground based transmitters
VOR ILS
164
an automatic pilot cutout will
remove the servo load
165
an AT engaged in the EPR mode will control
the engine throttles to maintain a constant engine power setting
166
an autopilot computer
is more sensitive to ILS than to VOR
167
an autopilot hardover runaway is caused by
loss of position feedback
168
an autopilot interlock circuit is to
both disconnect the system if a fault appears and prevent the system engagement if a fault exists
169
an AP PFCU servo brake is
energised off
170
an autopilot runaway is prevented by
torque limiting device
171
an AP servo motor is often fitted to a mounting plate to
enable motor replacement without disturbing flight control system
172
an AP synchronisation loop circuit must ensure that the trim system
disengages if hard over is detected
173
an AP transfer valve
converts electrical power to hydraulic power
174
an autopilot with two separate power supplies is
fail operational
175
API trim pointers are fed by
an LVDT
176
auto trimming trims the aircraft
by movement of either the elevator or stab
177
automatic steering of the aircraft after touch down is affected by
the runway localiser
178
automatic trim systems on some aircraft installations are actuated with two speeds of operation operation at high speed is used during
flaps down
179
automatic trimming starts on the detection of
standing load on the elevator
180
AP can be disengaged by
a switch on the control column another on the control panel and PFCU failure only
181
AP clutches are energised
on
182
AP controls roll on aircraft between
6-8 degrees
183
AP is making a stab trim adjustment which trim is now inhibited
mach/speed trim
184
AP servo brake is energised
to actuate off
185
AP will interface with which nav aids
VOR DME ILS
186
AP will operate above what altitude
500ft
187
AP go around mode is normally engaged by actuating a switch mounted on the
engine power lever
188
AP when on approach to landing how many axis are used
3
189
AT is controlled by what
AOA & flap position
190
auto trim is
a pitch function
191
back beam scanning in an MLS is at a rate of
20 degrees per millisecond
192
bank angle limiting in heading mode is via
servo position feedback
193
bank angle limiting is applied in which modes
heading mode LOC mode
194
basic monitoring is a function of signal comparison
signal comparison
195
before an aeroplane is able to make an automatic landinf the
ILS system must be working
196
capture of a localiser beam is normally dependent on a change of back angle command based on
ground speed
intercept angle
distance from beam
197
CAT 2 RVR is the alert height is 100ft will be 400m
400m
198
CAT 3B landing uptown what phase is LOC signal used
roll out
199
CAT 1 autoland DH limits are
not less than 200ft
200
CAT 2 autoland DH limits are
below 200ft but not less than 100ft
201
CAT 3B allows
approach land and runway guidance with taxing visibility in the order of 50m
202
coordinated autopilot turns are achieved by
aileron to rudder corssfeed
203
DH is based on
RVR transmitted by ATC
204
control loop gain with an autopilot is usually
dependent on aircraft altitude
205
during an automatic landing the aircraft decent rate is sensed by
rad alt
206
during an autopilot coordinated turn
ailerons, rudder and elevators will move
207
during autoland failure of one channel is detected
all channels will disconnect in a duplex system
208
during flare mode AT will
retard throttles to idle
209
during take off with AT engaged the AT sensor fails THR CLP is annunciated on the mode annunciator panel when
V2 as determined by the AT computer
210
during take off if an input to AT fails
throttle hold is annunciated
211
Fail passive means
system self monitors and the system has the ability to withstand a failure without endangering pax safety and without producing excessive deviations from the flight path
212
fail passive system fails what will happen
produce no out of trim and autoland is not completed
213
failure of an autopilot in flight will be indicated by
a failure light and an aural signal
214
feedback is
the reverse phase of the command
215
for an aeroplane to be certified for automatic landinf an AT system is
dependent upon the operation of the aeroplane at slow speed
216
glideslope controls autopiot in
pitch
217
glideslope gain programming is based on
rad alt
218
go around mode can be initiated
below 2000ft
219
gradient units or force gradient spring cylinders incorporated into some helicopter control systems
are unique to a specified control channel and are adjustable for the required tension
220
helicopters with AFC static droop is
change in stabilised RPM
221
high and low signal to voter are
removed
222
how can a pilot override the AT
manually through a clutch on the throttle levers
223
how can ambiguity be avoided during the test of a MLS
note scan cycle start time
224
how do the crew select decision height
selected on the rad alt display
225
how is automatic AOA protection provided
AT applying more power
226
how's is the stab automatically controlled in normal manual operation
mach/speed trim
227
if a fault is detected during an auutoland approach the system will totally disconnect if it is a
duplex system
228
if a series actuator is fitted in the cyclic control circuit of a helicopter what effecrt will an AP input have
the cyclic lever will not move
229
if an AP is fed with a radio deviation alone
it will fly in circles
230
if during autoland the LOC signal is lost at 400ft in final approach
a go around is initiated
231
if go around has been initiated after autoland has been selected the aeroplane will
increase speed and pitch nose up
232
if on an ILS approach LOC signal is lost
aircraft depends in a parrallel path to runway
233
if only radio deviation is fed to the AP roll channel what will happen.
aircraft will fly in circles
234
if the AP automatically disconnects in the autoland mode the audible warning
is switched off by the instinctive cut out button
235
if the LOC signal only is applied to the AP roll channel
aircraft flies in circles
236
in a helicopter the rate gyro and leak integrator inputs which are fed to the computer form part of the
inner loop control system
237
in a helicopter altitude hold uses a signal from
the barometric alt capsule
238
in a servo loop an LVDT provides
position feedback
239
in a simple VS hold circuit the clutch is
engaged only when the VS mode is engaged
240
in a tripple AP system failure of the ILS receiver before alert height will result in what
initiation of a G/A
241
in a triplex system if an ILS receiver fails before LOC capture
there is no autoland
242
in a triplex system loss of one ILS receiver signal after alert height would result in
a full autoland continued
243
in a triplex system loss of one ILS receiver signal before alert heigh would result in
a go around initiated
244
in a triplex system the detection of a failure of one simplex system will disconnect
the failed system and carry on with the autoland
245
in aircraft with an AP and an auto trim a pitch command input will cause
column to move and trim system to move
246
in an auto trim system for the trim system to operate
autopilot need not be engaged
247
in an AFCS whose control channels can be engaged with PCUs the appropriate command signals control the operation of a transfer valve which
positions a spool valve to supply hydraulic fluid to the main actuators
248
in an autoland AT is disengaged
after reverse thrust is applied
249
in an AFCS when may the yaw damper be applied
during either manual or automatic control
250
in an autopilot that controls pitch mode
glideslope
251
in an AT system when is EPR or thrust mode used
Take off
252
in AP with THS in motion the
auto trim is inhibited
253
in AP the control column
moves in pitch and roll
254
255
in flight with the pitch channel engaged to the autopilot the signal from the vertical gyro will
always oppose the pitch command signal
256
in helicopter autopilots while operating the actuator the movement of the cockpit control is prevented by
a compressed spring attached to the cockpit control
257
in ILS the glideslope provides
vertical steering
258
in the electro pneumatic servo-motor using dual poppet valves and dual roll frame actuator when there is zero command output from the AP servo amplifier
both valves will ve open for an equal period of time
259
in the FMS VNAV climb mode the throttles are used for
maintaining a computed EPR
260
in triple AP system failure of the ILS after alert height will result in what
continue autoland
261
in triplex autoland system failure of one channel will
disconnect the failure channel and continue autoland approach
262
inner loop servo control of an AP will provide
stability only
263
loss of course washout signal whilst on LOC approach would result in
continued flight on course but with scalloping or bracketing
264
minimum operating speed of the AT is derived from the
AOA
265
MLS azimuth range is normally +/- 42
+/- 42
266
on a cat 3B landinf the LOC signal is used at which phase
rollout
267
on a coupled approach what happens to the aircraft if it loses localiser signal
it will fly on the heading the aircraft was on
268
on an autoland during auto flare it will
retard the throttle
269
on an ILS approach what will cause the aircraft to fly onto the beam
radio deviation
270
on LOC approach the radio deviation signal is lost
aircraft flies off centre line on pre set heading
271
on receipt of a radio signal which type of circuit would be used to wash out the information
integrating circuit
272
on replacement of an actuator that incorporates an AP actuator the AP must be checked fo
correct sense and range of movement and AP breakout
273
on replacement of an AP servo motor
torque limiting settings must be checked
274
on selection of the turbulence mode
the gain is reduced to prevent stresses to the airframe
275
on the approach the AP loses the LOC signal the aircraft would
fly parallel to the beam
276
on the ground failure of the AP servo motor rate feedback will cause
occiwslations of the control surface about its datum position
277
on touch down the auto throttle
disconnects after a short time
278
once the G/S has been captured what other pitch modes are available
no other pitch modes are available
279
one basic requirement of a synchronising loop is that it must
disengage as soon as hard over is detected
280
operation of the yaw damper test switch in the cockpit will cause the
pointer in the trim indicator to move
281
oscillation and hunting of flight control surface are prevented by
use of a tachogenerator
282
overshoot or go around mode can be initiated
at any time after autoland has been engaged
283
pitch trimming in AP is initiated by
continued pitch input
284
purpose of an autoland decrabbing maneovre is to
point the aircraft down the runway at touch down
285
rate feedback signal in a rate/rate system
provides proportional response to commanded inputs
286
reverse thrust us selected
after disengagement of the AT
287
roll out guidance us used
after flare
288
roll out mode occurs
after flare
289
roll out guidance after touchdown is by
automatic rudder control and nose wheel steering
290
roll out guidance by the rudder is effective to about
80k
291
RVR is obtained by
three sets of instruments at the side of the runway
292
selecting a profile for VNAV for AT speed control
can be done at any time
293
signals used during the flare are
rad alt and integrated pitch
294
speed information to the AT is derived from
the CADC
295
stand off errors on LOC approach are washed out by
integrating course error signals
296
synchronisation circuits in AP ensure
that the AP control circuits are at zero demand conditions on engagement
297
the aeroplane AP is programmed to leave the GS at
start of the flare phase
298
the AFCS remains in control
until disengaged by flight crew
299
the aileron/rudder signal is demodulated in the rudder channel amplifier this means It is
DC output whose polarity is related to the phase of AC input
300
the aircraft decorating signal used during autoland originates from
heading errors
301
the airworthiness requirements for the autopilot / autobahn system are laid down in
JAR AWO
302
The AP disconnect annunciator is
a red caption
303
the AP is instructed by the
FMC
304
the AP prevents adverse yaw by
aileron to rudder cross feed
305
the AP will automatically disengage if the
VG fails
306
the automatic stab is for
removing standng loads
307
The AT system at touch down will
go tio idle and disconnect
308
the AT controls the aircraft
vertically
309
the average risk of autoland should not contribute a rate of fatal accidents per landing greater than
1x10-7
310
the components of an ILS are
a localiser glide slope and marker beacons
311
the controlling signals in pitch channel in the flare mode are
integrated pitch and rad alt
312
the DH in the rad alt system is adjusted by
moving a bug on the Rad alt indication
313
the definition of fail operational is the ability of a system to
continue to control after any first fault
314
the effective gin of the glide path receiver
is decreased as the aircraft depends
315
the facility performance ILS intersect height is the point
the localiser and glide path signals cross each other
316
the flare manoeuvre may be controlled by signals from
rad alt
317
the following modes may be retained when overshoot has been initiated after the selection of autoland
IAS and steering or heading
318
The GA mode us usually initiated by
pressing a button on thrust levers
319
the glides
glideslope signal
320
ICAO weather category 3A is
operation down to and along the surface of the runway with RVR of 200m
321
the ingretiy of an AP must be increased when the aircraft is flying at
approach and landing phases
322
the maximum azimuth coverage by a MLS facility is
+/- 60 degrees
323
the order of autoland approach is
LOC
GS
ATT hold
FLARE
324
the outputs of a slaved directional gyro to an AP consist of
azimuth direction information
325
the overshoot or go around mode is initiated
by a selector on the throttle control panel
326
the pilots instinctive AP disengage button is on the
side of the controls away from the throttles
327
the purpose of a force trim release system in a helicopter is to permit the
pilot to move the cyclic stick to obtain desired new attitude without having to maintain the opposing forces of the artificial feel system forces
328
the purpose of the AP servo motor torque setting is to
prevent control surface runaway
329
the purpose of the clutch in an AT servo is
to allow the pilot to override
330
the purpose of using altitude rate signal to develop the capture point in the alt acquire mode is
to allow the aircraft to start flaring on to the selected altitude earlier if the vertical speed is high
331
the radio nav systems which may be coupled to an AFCS are
VOR ILS
332
the time reference scanning beam corresponds to ILS localiser and glide path how does it operate
azimuth and elevation transmitters produce a narrow beam which is rapidly scanned TO and FRO or UP and DOWN 1
333
the two parameters used for category classification are
DH and RVR
334
the type of amplifier used to overcome difficulty frequency signals and to prevent drift is
chopper amplifier
335
the wheel height at which the approach path has been visually assessed as satisfactory to continue the approach to a landinf is known as the
DH
336
the yaw channel of an AP system is commanded by
the turn coordinator circuit
337
throttle hold will occur
at a predetermined take off speed
338
to carry out an autopilot check first
ensure all control surfaces are unobstructed
339
to ensure an aircraft attains the glideslope track
there is a GS capture bias applied for 10 secs after the system switches to capture modet
340
to increase the gain of an amplifier it is neccasry to
reduce the tachogenerator feedback
341
to prevent an aircraft standing off from a selected radio beam due to cross wind it is usual to
introduce an integrator in parallel with the course error signal
342
torque is limited by the clutch in the servo motor to
allow the pilot to override the AP
343
touch down mode is initiated by
AOA and flap position sensor
344
versine is attenuated with
IAS
345
Versine is used in which channel
pitch
346
VNAV can be selected
alone
347
VOR signals are sent to the
roll channel
348
what channel of the AP does the GS control
pitch
349
what class of amplifier processes less that 180 degrees of a signal
class C
350
what is added to the flare computation at touchdown
nose down bias
351
what is B-RNAV
indicates bearing and airspeed until next active waypoint
352
what is the controlling factor in the automatic flare mode
Rad alt
353
what is the GS freq range
329-335MHZ
354
what is the main operating principle of MLS
time difference between TO & FRO pulse
355
what is the maximum sweep angle of an MLS installation
+/- 62 degree
356
what is the purpose of the AP trim indication
indicate the voltage activity in the servo amp
357
what type of signal is used for trigger height trip signals
switchable DC
358
when a deadzone amplifier is used a CWS circuit
passes only signals above a certain magnitude
359
when can other AP modes be selected once go around has been selected
when reached a desired altitude
360
when can the FMS be engaged with the AT
only after takeoff
361
when carrying out an autoland approach VNAV is deselected the aircraft will enter MCP SPD mode when
the aircraft captures the glideslope
362
when DC motors are used as servo motors they are usually
spilt field type
363
when down grading an autoland system what needs to be done
an entry in the log book and cockpit placarding
364
when GA is initiated
AT remains engaged giving correct G/A thrust
365
when internal navigation control is used the roll channel signals used are
cross track distance and track angle error
366
when is AT disengaged
in selection of thrust reverse
367
when pitch angle limit is used it is applied during altitude hold mode to the
pitch attitude signal
368
when the AP is engaged moving the control column forward will cause the pitch CWS sensor
to produce a significant signal which has pitch down sense
369
when the AT is selected to airspeed more the throttles will maintain the
speed selected on the thrust select panel
370
when the bank angle limit is applied to the AP it means
the maximum roll angle that can be demanded ny the AP
371
when the rotor of an AC tachogenerator is stationary the rotor has
circulating currents
372
when turn mode is selected which other mode will not available
ALT HOLD
373
when will the DH aural warning sound
before DH
374
where is the AT disconnect switch
within reach of both pilots
375
which is the correct sequence for an autoland
LOC
GS
ALT HOLD
FLARE
376
which modes are incompatible
GS + ALT HOLD
377
which modes are incompatible
VOR & GS
378
which of the following is correct
error = demand - feedback
379
which of the following modes does an AP go through in correct seq
attitude
flare
rollout
380
which signal would be integrated to get onto LOC CL
radio deviation
381
with a fail passive system in the event of failure it will
produce no significant out of trim condition
382
with AT engaged the application of reverse thrust will
disconnect the AT
383
with the AT selected in the speed mode compatible AP modes are
VOR ARM & HDG HOLD
384
with CWS if the flight path is disturbed by the pilot the course will be corrected by the
autopilot panel
385
with heading mode selected and in a coordinated turn the roll channel responds to the heading error signal
opposed by a vertical gyro
386
with power applied to the AP but not engaged the trim indicator will indicate
a standby electrical signal in the servo loop
387
