Instrument Q’s Flashcards
(570 cards)
1
Q
Liquid crystal displays
A
Are negatively affected by low temperatures
2
Q
Deviation on N deviation on S / 2 is
A
Coefficient C
3
Q
What is deviation
A
Error Inherent in a magnetic compass
4
Q
An instantaneous VSI is connected to the
A
Static pressure only
5
Q
As per eu ops 1.160 following an accident or incident the data pertaining to the event shall be recorded and rained for a period of
A
60 days for both
6
Q
A +/. Symbol on a compass system indicates
A
Compass card and directional gyro are being synchronised
7
Q
The DFDR is able to accept inputs directly from certain systems under what situations can the DFDR accept this data
A
System data must be in a format that is recon used by the DFDR
8
Q
A single rate gyro can be used to sense attitude about
A
2 axis
9
Q
The output of an E and I bar sensing device is
A
Phased sensed AC
10
Q
Non magnetic proximity sensors should be checked
A
In the near condition
11
Q
How is EPR measured
A
The ratio of compressor inlet pressure and the exhaust pressure
12
Q
An artificial horizon gyro has
A
Three degrees of freedom and 2 gimbals
13
Q
A boost gauge reads
A
Absolute pressure
14
Q
A null indicator is a
A
Moving coil meter
15
Q
An attitude gyro disturbed in pitch would apply a corrective force through the pitch motor acting between the
A
Outer gimbal and case
16
Q
A category 2 approach has a decision height of 100ft and an RVR of
A
300m
17
Q
A category 2 approach requires
A
A rad alt and an ILS coupled autopilot
18
Q
For a rate gyro to detect roll movement its axis of spin must be
A
Athwartships
19
Q
Vacuum systems can be used for
A
Instruments having an air driven gyro
20
Q
A centralised warning panel process warnings, cautions and advisories/indications as follows
A
Red warnings
Amber cautions
Gren blue or white advisories/ indications
21
Q
An AOA sensor is used for
A
Alpha protection
22
Q
To leak test a vacuum system
A
Blank system inlets operate a vacuum pump stop the pump and check leak rate
23
Q
A vertical gyro used as an artificial horizon has
A
1 gimbal with 2 axis of freedom
24
Q
Temperature compensation in a servo altimeter is achieved by
A
Increasing the tension in the hair spring
25
A combined ASI indicates Mach
All the time airspeed is present
26
The dip angle at the equator is
0 degrees
27
An RMI would use for the displacement of the indicator needle
ADF & VOR
28
In order to check the turn indicator for correct operation dismount the indicator and check it against the
Horizontal axis
29
A compass has a residual deviation of + 1 degrees
To fly a heading of 180 degrees the pilot must steer
179 degrees
30
A vertical gyro senses disturbances in
2 axis
31
An OAT gauge when flying at a constant altitude if the airspeed was to increase the OAT indication would
Increase
32
A compass is made a periodic by
Using fluid
33
A compass shows 000 deviation is +2 after comprenant a is added heading is
358
34
A vacuum pump in an air driven I stringent system draws air
Through a filter into the instrument canes then into a pump where it is discharged overboard
35
A compass swing would be required after replacing a
Compass sensing unit
36
A compensatior capacitor in a capacitive fuel I dictation system is
To detect changes in dielectric constant due to temperature changes
37
A constant for e applied to the inner gimbal of a vertical gyro would cause
A continual precision roll
38
A direct reading compass fitted on an aircraft the safe distance for electrical cables carrying electrical current is
24”
39
A DC electrical cable must be postions
How far away from
A compass
24”
40
A densitometer in a capacitive fuel indication system measures
Density of the fuel by measuring the natural frequency of a vibrating spool
41
a desiccant used in the storage of instruments
is silica gel
42
a direct lift system using a floating magnet and reed switches measures
fluid volume
43
a direct reading bourdon gauge has a restriction in the inlet this to
dampen sudden pressure changes
44
a direct reading compass reads 000 degrees and after applying coefficient A if +2 degrees it should read
002 degrees
45
a FDAU transmits data to the flight data recorder by
ARINC 573/717 data bus
46
a FDR is activated when
the helicopter engines are started
47
a flux detector output is
AC voltage at twice the freq of the excitation voltage
48
a flux valve become permanently magnetised what will be the effect
more deviation
49
a force balance system using a capsule will produce an output which
is in opposition to capsule expansion
50
a fuel flow measurement system
cannot be adjusted
51
a fuel quantity test set consists of
capacitance bridge
52
a fuel system that corrects fuel SG is calibrated in
Lbs or KGS
53
a fuel system that ensures SG will be displayed in
Lbs or KGS
54
a gate valve is installed in a vacuum system to prevent
reverse flow fue to engine backfire
55
a garage pressure of 1 atmosphere is an absolute pressure of
2 atmospheres
56
a glass cockpit system on a modern aircraft primarily consists of
a PFD & multifunction display (or nav display)
57
a gyroscope having one plane of freedom at right angles to the plane of rotation and its gimbal restrained either electrically or by a spring is known as
a rate gyro
58
a gyroscope with a vertical spin axis has the roll torque motor located about the gyroscopes
lateral axis
59
a gyroscopic body has its rigidity increase by
increasing the rotor speed
60
a laser ring gyro gives
rate of angular displacment
61
a leak in the static line in a pressurised part of an aircraft can cause the mach indication to
decrease
62
a mach meter
compensates for square law
63
a mach meter is
compensated with square law screws and an arm
64
a mach meter reads the correct value
at any altitude
65
a mach meter transduces
airspeed and altitude
66
a mach meter
has adjustment screws for the purpose of square law calibration
67
a mach meter works
always
68
a master warning is issued when
overspeed and excessive cabin pressure altitude occurs
69
a pendulous vane type erection system fitted to a gyro horizon works on the principle of
increase reaction of the air from a fully open port
70
a pito static leak check is carried out
whenever the pitot static systems are disturbed
71
a pneumatic indicator takes its indications from
reservoir
72
a positive coefficient A adjustment of a compass will give a heading
increase on all headings
73
a pressure gauge such a a hydraulic break pressure gauge indicates 1000psi in terms of absolute pressure this represents
1014.7 psi
74
a pressure of on atmosphere is equal to
14.7 psi
75
a radio altimeter system can be self tested
on the ground only
76
a rate gyro has
a calibrated spring between inner gimbal and case
77
a rate gyro has how many degrees of freedome
1
78
a rate two turn is
360 degrees per minute
79
a radiometer uses
current input and output
80
a remote compass compensator unit is replaced which of following us correct
a comopass swing must be performed
81
a sensitive altimeter reading 100ft when the millibar scale is set to the atmospheric pressure at airfield level (QFE)
indicates that the instrument is unserviceable
82
a silica gel desiccant is require to be replaced w
when all pink
83
a standby ADI use
a vertical gyro
84
a small constant leak in the case of VSI fitted in a pressurised aircraft would during level flight cause the instrument to indicate
a rate of climb
85
a standby air supply for gyro operation could be obtained from
a venturi
86
a standby artificial horizon uses a
earth gyro
87
a standby compass has a pair of magnets for adjustment they are initially placed
parallel with each other
88
a tacho generator has
its own independent electric system
89
a tacho generator pointer is moved by
a drag cup coupling
90
a temperature bulbs resistance is
directly proportional to temperature
91
a temp of 59F is equivalent to
15C
92
a thermo couple
cannot be shortened
93
a turn and slip needle points to the left when the aircraft is
turning left
94
a turn and slip needle/pointer moves to the left what is the aircraft doing
turning left
95
a typical radiometer indicating system would use
single phase AC for indicator and transmitter
96
a unit with two springs and a mass pick off is
an accelerometer
97
a VSI is connected to
static pressure
98
a vacuum mercury gauge reads 5 in this pressure is
below ambient pressure
99
a vertical gyro used for autostabilisition the roll attitude will be limited in
heading and localiser mode
100
a VSI metering unit consist of
both an orifice and a capillary
101
a drag cup type of tacho generator system used for indicating the rev/min of a turbine engine has
an indépendant electrical system
102
above 2500ft the Rad alt
pointer is hidden behind a ask with off flag out of view
103
absolute pressure of 25psi is
10.3psi
104
acceleration error produces
a false indication of climb
105
adding 3ft of cable to both TX & RX aerials on a rad alt would give you
9 feet error
106
after correction of the north south heading reading on a compass swing the resultant correction is known as
residual deviation
107
after disconnecting the supply to an electrically operated gyro instrument it is recommended that to allow the gyro rotor to stop before moving the instrument
15 mins should elapse
108
after replacing an instrument of the pitot static group it is neccassry to
carry out a leak test on the appropriate systems
109
after the compass has been corrected for Coefficient A, B & C the remaining error is known as
Residual Deviation
110
after using a pitot static test set the pressure in the aircraft static system should be released to the atmosphere by
venting the static system via an internal bleed in the test set
111
agonic lines link places of
zero variation
112
air density compensation requires
altitude and OAT
113
air driven gyros compared to electric gyros generally rotate
slower
114
aircraft certified before 1997 with RVSM maximum tolerance for the system is
+- 300ft system & +- 50ft for instrument error
115
aircraft heading HDG is
the angle between true north and the longinutdal axis of the aircraft
116
aircraft instruments are classified into three categories
flight instruments engine instruments navigation instruments
117
all fly to information in an EFIS system is displayed in
magenta
118
alpha angle relates to which system
angle of attack system
119
alpha vane signal could be fed to _ _ when close to stall
thrust levers
120
an absolute pressure gauge measures
the applied pressure referred to a perfect vacuum
121
an aircraft ASI has
pitot to the capsule and static to the outside of the capsule
122
an aircraft in climb maintains the same IAS what it its true airspeed
higher than its IAS
123
an aircraft increases in altitude the ASI indication remains constant what will happen to the true airspeed value
increase
124
an aircraft landing on QFE the altimeter will
read zero on touchdown
125
an aircraft magnetic compass is swung to update the compass correction card when
equipment is added that could effect compass deviation
126
an aircraft that is being rectified for RVSM will require
a flight test verification
127
an aircraft with mach warning will warn
when Mcrit is reached
128
an airspeed indicator responds to changes in
dynamic pressure
129
an altimeter consists of
a barometric scale adjustment
130
an altimeter in a pressurised aircraft at altitude has a case leak the altimeter will
under read
131
an altimeter is operated
by the static system
132
an altimeter on ground check reads slightly outside permitted tolerance
an in situ adjustment can be carried out
133
an articial horizon has
the inner gimbal pivoted laterally
134
an artificial horizon uses
a vertical gyro
135
an artificial horizon will have a corrective torque applied
at 90 degrees before the axis in which the correction is required
136
an ASI compressibility error correction will be negative
negative
137
an ECAm system is tested under the following conditions
aircraft on the ground with parking brake set/on
138
an electrical gyro has usually a speed of
20,000 rpm
139
an electrically operated standby artificial horizon
requires an emergency power supply
140
an engine vibration indicator system uses
2 filters in the indicator
141
a letter H displaying on the EHSI indicates
DME hold
142
an HSI provides what information
VOR, PLAN, ILS, MAP, RADAR
143
an ILS indicator is
across filters
144
an important air data used with the IRS is
TAS
145
an increase in forward speed at a constant throttle will result in EPR
Decreasing
146
an instantaneous VSI indicates instant values of VS by
using a plunger to correct any lagging of the indicator
147
an instrument used for measuring negative pressures
has anti clockwise pointer movement if bourdon tube operated
148
an open circuit in the temperature bulb as used in the DC radiometer would cause
the pointer to read full scale
149
an RMI has inputs from VOR and
azimuth gyro
150
an RMI requires the following inputs
heading and radio deviation
151
an uncorrected ADI is affected by
roll
152
aneroid capsule measure pressure with respect to
a vacuum
153
AOA alarm is sounding to close to stall rectification is to
move probe up
154
angular momentum of a gyro rotor depends on
moment of inertia and angular velocity of the rotor
155
apparent drift of a vertical gyro is a function of
COS of latitude
156
apparent drift on directional gyro its corrected by
an adjustment nut on inner ring
157
as part of the checks on the DFDR system you are required to carry out a check using the self test switch on the AIDS printer actuation of the switch causes the printer to print in
forty column mode
158
at the lowest point of each vent line you would normally find a
self draining non return valve
159
at what height does the rising runway appear
200ft
160
at which two points on a gas turbine engine is EPR measured
compressor inlet and jet pipe
161
Bourdon tube have
oval cross section
162
brake temperature readings provide
coloured indications on a CRT display
163
capacitance fuel quantity indication test set is connected
by replacing capacitance probes
164
capacitors in a capacitance fuel contents indication system are wired in
parallel
165
Coefficient A correction is carried out
after B and After C
166
Coefficient A is adjusted
on any heading
167
compared to air driven gyros the electric gyro runs faster
faster
168
compase base classification class 2 is periodically re-surveyed every
2 years
169
compass compensator units have greatest effect when the magnets are
90 degree apart
170
Compass error Q corrections correct
C Error
171
Compass error remaining after all the corrections which is used for entry on the deviation card should not exceed
3 degrees
172
Compensator magnets in a standby compass exert greatest influence at
90 degree to each other
173
Coefficient C is
(DEV on N - Dev on S)/2
174
Componenet P affects
Coefficient B
175
Compressibility error in a pitot head is caused by
compression of air in the tube at high speed
176
corrections to a mechanical ASI are for
square law error and temperature
177
cyclic shift of the gator connections in a torque sychro results in
output datum advanced 240 degree
178
Damping on a rate gyro can be either
viscous eddy current or air dash pot
179
data collected by FDAU can be divided into two categories
mandatory and ACMS
180
Deviation from the HSI lubber line is known as
apparent A
181
DFDAU received aircraft parameters are of analogue, discrete or binary digit from the
aircraft systems
182
digital weather radar is on map mode what happens
antenna tilts down
183
during a change to a Lower altitude the piston unit in an IVSI will creat for an instant
more pressure to the capsule only
184
during compass swing using a data compass the error permitted in aligning the aircraft is
5 degree
185
during a coordinated turn a pendulous suspended flux detector will assume the angle of
dynamic vertical
186
during climb the pressure in the VSI capsule will be
lower than the pressure in the case
187
EFIS display SG1 + SG2 are for the captain and FO displays what is the purpose of SG3
Back up for SG1 & 2
188
EGPWS mode 2 announces
whoop whoop pull up
189
EICAS indicates
engine performance and aircraft status
190
EICAS provides the following
engine parameters and system warnings
191
EICAS EFIS ECAM are all terminologies applicable to
Glass cockpit instrumentation
192
electrical driven gyros are
rotated faster than air driven gyros
193
Elimination of vibration in the instrument panel is by use of
shock mounts
194
EICAS displays alert messages on the
Primary EICAS display unit
195
Engine vibration signals are
filtered to remove unwanted frequencies
196
Equivalent airspeed is
calibrated airspeed corrected for compressibility
197
FDR data is stored on
semiconductor memory
198
Flight director bares move up in slow increments what controls their rate/speed
rate feedback
199
Flight director command bars indicate
direction in which aircraft is to be manoeuvred
200
Flight director incompatible modes are
VOR & glideslope
201
following replacement of a seperetly mounted compass corrector box a compass calibration swing will be required
without exception
202
for a given IAS with an increase in altitude TAS will
increase
203
for a particular IAS as the density decrease with altitude the TAS
increases
204
for a vertical gyro which is moved in pitch which gimbal would be moved to correct the pitch movement
longnitudanal
205
for aircraft certified after 1997 and with RVSM the maximum tolerance for the system would be
+- 200ft plus +- 50ft for instrument error
206
Fo ran EGPWS to indicate predictive wind shear it needs an input from
weather radar
207
Fuel tank units (capacitcane) are connected
paralell connection
208
Gauge pressure as indicated on a direct reading bourdon tube pressure gauge is equal to
absolute pressure minus atmospheric pressure
209
gimbal lock in a displacement gyro occurs when
spin axis becomes coincident with any of the axis of freedom
210
GPS runs on which band
L band
211
GPWS inop light comes on engineer would initially
do a level 2 self test to determine the source of the fault
212
GPWS is
C Band
213
GPWS mode 1 is excessive
rate of decent
214
GPWS mode 7 provides what warning
windshear
215
GPWS mode 7 wincher is activated at
1500ft rad alt for take off and for landing
216
graphics generators
are fitted to aircraft that have CRT/Flat screen displays
217
Gyro precessional force is
directly proportional to applied force
218
Gyro rigidity is proportional to
mass speed and radius of mass from spin axis
219
How are direct reading compasses calibrated
mechanical magnetic compensator assembly is adjusted to counter stray magnetic field influence
220
how do you detect and locate a leak in a pitot static system
pressurise the system and use the soap bubble detection method
221
how does a Machmeter work
TAS and speed of sound
222
how is a direct reading compass made to be aperiodic
the compass bowl is filled with fluid
223
how is leading edge flap position indicated in the cockpit
Torque sychro
224
how is temperature compensation achieved in the fluid of a compass
bellows and diaphragm
225
how is the gyro aligned in a rate of turn indicator
it has a horizontal spin axis aligned laterally
226
how is the information on a directional gyro outer gimbal taken off
by a flux take off device
227
how may the basic principle of the rad alt be described
as a measure of the time between a RF pulse transmission and the reception of its echo from the ground directly below the aircraft
228
How should an operating gyro be caged
by pulling the caging knob with a steady action
229
ICAO standard atmosphere
taken from data measured at 45 degrees north
230
if a constant torque is applied to a gyroscope the rate of precision
increases with a lower rotor speed
231
if a drain trap in a pitot static system is removed but nothing was found
a leak test must be carried out even if nothing was found
232
if a micro adjuster is replaced in a compass system you would
carry out a new compass swing
233
if a QFE is set at an airfield and flown to another airfield at the same level above sea level then
it will probably not need resetting and will read zero
234
if an aircraft flying in still air at 400k encounters a head wind of 50k its ground speed is
350k
235
if an aircraft is flying straight and level in still air airspeed will be
equal to the ground speed
236
if an aircraft lands on QNH what will the altimeter read
elevation above sea level
237
if an altimeter millibar scale was set to 1013.25mb and the barometric pressure at that time was 1020mb the altimeter should read
below zero feet negative altitude
238
if increasing altitude at constant IAS TAS will
increase
239
if one FMS fails in a dual system
FMS CDU on fail side goes blank
240
if rate feedback in a flight director goes open circuit position indication will
oscillate
241
if the ASI reading is 300K what is the calibrated airspeed
304K
242
if the compass fluid has bubbles at low altitude
this is due to insufficient de-aeration
243
if the pitot and static pipe lines were cross connected at the instrument panel connection application of pressure to the pitot head would cause
altimeter reading to decrease VSI to indicate a decent
244
if the static line is disconnected in the cabin of a pressurised aircraft when the aircraft is flying in the stratosphere the mach meter reading would be
lower than the true mach number
245
if the static line is disconnected in the cabin the mach meter reading would be
lower mach number
246
if the static pressure is varied at too great a rate the instrument that is most affected is the
rate og change indicator
247
if the static vent is leaking into cabin pressurised space when the aircraft is at altitude a mach meter will indicate
a decrease
248
if the static vent line starts leaking into cabin pressurised space when the aircraft is at altitude above 8000ft a mach meter will indicate
a decrease
249
if the torque were increased on a vertical gyro what would happen to the precession
increase
250
if TAS is 470k what is the equivalent air speed
278k
251
if during auto land the GPWS fails
there is an aural plus visual warning
252
in a 28 volt AC curent ratometer pressure indication system pointer position is determined by
the difference between two currents in the indicator field windings
253
in a boost gauge system the sensing element contains
2 capsules
254
in a bourdon tube
one end is sealed and the other end open to the pressure source
255
in a capacitive fuel contents system changes in temperature are compensated by
placing a capacitor in parallel with the tank unit capacticane
256
in a capacticane fuel gauging system an increase in fuel level would increase capacitance
increase capacitance
257
in a central ADC IAS is produced from
Pitot and static air pressure
258
In a ADC the rate of climb of an aircraft is produced in the
altitude mode
259
in a ADC system mach information is derived from
indicated airspeed and altitude
260
in a CADC system TAS is derived from the Mach information and
total air temperature
261
in a CADC altitude is produced from
static air pressure
262
in a combined pitot static probe while carrying out a leak check which instrument is most likely to be effected by over pressure
VSI
263
In a compass swing
north error -2 degrees
south error -2 degrees
the coefficient C is
0 degrees
264
in a compass swing
north error -2 degrees
south error +2 degrees
the coefficient C is
-2 degrees
265
in a compass system tilt error us compensated by placing magnets
below the pivot point
266
in a compass system what senses the horizontal component of the earths magnetic field and where is it normally fitted
flux detectors fitted in the wing tips
267
in a digital radar display system the position of the line and field timebase waveforms
must be the same as the X-Y memory read address
268
in a directional gyro the inner/outer gimbal is corrected to
15 sine latitude
269
in a dual FMC installation if one FMC is defective
one CDU blanks
270
in a flight director system the radio signal outputs from the navigation receiver are
DC
271
in a float type fuel system calibration must be done
with tanks empty
272
in a horizontal gyro the random precision of the inner ring is corrected by
flux valve slaving
273
in a tachometer what type of compensation is there
square law compensation
274
in a MCDU the flight deck effect is
any EICAS display or discrete annunciator to inform the flight crew of an in flight fault
275
in a modern HSI the splays are course and direction
course and direction
276
in a ratiometer temperature indicatijng circuit there is a break in the circuit to the bulb this will give
full scale deflection
277
in a turn and bank indicator in a coordinated turn the pendulum will be in the ____ position
dynamic vertical
278
in a turn and slip indicator the effect of increasing the rotor speed would be
it would under read
279
in a turn coordinator the output axis of the rate gyro is
set at 30 degrees to the longitudinal axisi
280
in a vertical horizon gyro the inner gimbal ring should align to the
vertical axis
281
in air speed hold mode a down displacement of the flight director pitch command bar signifies
speed decrease
282
in airways flying what is the barometric scale of the altimeter set to
1013.25mb
283
in an altimeter the
capsule is evacuated and sealed
284
in an artificial horizon pendulosity error is caused by
bottom heaviness of inner gimbals
285
in an artificial horizon errection errors caused by
displacement of erection control device
286
in an EICAS display all scales normal operating range of pointers and digital readouts are displayed in
white
287
In an EICAS level C messages are
advisories and displayed in amber or light blue
288
in an EICAS system operation of the cancel swithch
removes caution and advisory messages
289
in an FDS the attitude gyro is coupled with the FD computer by means of transformer coupling the purpose of this arrangement is
to protect FD computer in case of attitude gyro failure
290
in an RVSM system what is the tolerance level of separation
80ft
291
in a DFDR system low speed playback of currently received data can be achieved at
the flight compartment test connector through the DFDAU
292
in HUMS systems what is used to pick up vibration levels
accelerometers
293
in level flight a VSI will indicate
horizontal left
294
in MLS the azimuth sweep rate is
20 degrees/ms
295
in RVSM the error allowed is
80ft
296
in the basic T instrument config
the directional gyro is below the attitude indicator
297
in the directional gyro
the outer gimbal is pivoted vertically
298
in the earths magentic fuel the term inclination is
the bending of the earth magnetic flux lines near the poles
299
in the Q code system QFR is the atmospheric pressure
at aerodrome level
300
in the Q code system QNH is the atmospheric pressure
at mean sea level
301
in the turn and slip indicator
the spin axis is lateral
302
index error is
misalignment of compass lubber line
303
inertia is
the property that resists any force that tends to change the plane of rotation of a gyroins
304
instruments used on an aircraft are in some instances fitted with cover glasses whose surfaces are bloomed to reduce
surface reflection
305
isogonal lines link places of
equal variation
306
JAR OPS states that the time an FDR recording must be kept after an accident or incident
60 days
307
leakage of a static line during a pitot static test alt increase would be indicated by
VSI remaining in a fixed position
308
limit stops are fitted in an artificial horizon to
prevent gimbal lock
309
mach metered work on
pitot and static
310
magnetic heading errors will be
positive is easterly
311
magnetic variation is the difference in angle between
true north and magnetic north
312
millibar is used to express what kind of pressure
barometric pressure
313
Mode S has
24 address bits
314
normal vertical minimum seperation allowed is
2000ft
315
on a conventional RMI the angle between the compass datum and the radio pointer arrow is the relative bearing
the relative bearing
316
on a flight director VOR ground test the deviation bar moves in relation to
actual heading set course and radio deviation
317
on a modern aircraft flight instrument display system radio deviation is shown on
EHSI & EADI
318
on a modern EFIS
The PFD is configured in the basic T layout
319
on a turn and slip indicator the needle points to the right and the ball us to the left the aircraft is
underbanked skidding out of the turn
320
on VSI fitted on an aircraft for climb and decent indication
a set screw is provided for zero adjustment
321
on an autoland coupled approach a GPWS warning
would be an audio and visual warning
322
On EADI the command bars show the
required flight path compared with aircraft position
323
on descent the pressure in a VSI capsule
leads the case pressure
324
on replacing a pre-indexed flux valve you would
fit the serviceable pre indexed flux valve into the same position as the US valve
325
on small helicopters how is the pitot heat system powered
when the generator is online
326
on the CWP what does amber indicatie
cautionary info
327
one atmosphere is
760mm.hg
328
one dot VOR deviation represents
5 degree
329
piezo works on the principle of
a voltage is produced by a force
330
pitot pressure is also known as
total pressure
331
pitot tubes are heated
electrically
332
pitot static lines in helicopters
must provide accurate information over the helicopter certified flight envelope
333
position error is caused by
pitot head position
334
precession of a gyro depends on
both movement of inertia and angular velocity of the rotor
335
pressure may be expressed in
force per unit area
336
pressure measuring instruments and systems are categorised into these three types
absolute gauge and differential types
337
priority message in an aircraft centralised warning system go in order of (lowest to highest)
TCAS GPWS Windshear
338
purpose of altitude alerting is to warn the pilot of
approach to or deviation from selected altitude
339
RAD alt uses what frequency
4000MHZ
340
radio marker information is displayed on
ADI
341
random drift of a gyro is caused by
gyro friction and unbalance
342
rotation of the barometric scale setting knob on a mechanically operated altimeter
causes the pointers barometric scale and capsule assembly to rotate
343
slat asymmetry may be monitored by using
position pick offs
344
standby compass adjusting magnets exert the most amount of influence
when 90 degrees apart
345
TAS uses which inputs
Mach and temperature
346
temperature compensation is required on an altimeter because of
capsule elasticity
347
temperature correction in a sensitive altimeter mechanism is provided by a
bi metal u spring acting on the capsule
348
the excessive bank angle aural alerts are given twice and then suppressed unless the roll angle increases by an additional
20%
349
THE AC Emergency instruments are fed from which bus?
AC essential bus
350
the advantage of an instantaneous VSI over a conventional one is
it has an accelerometer which prevents the lag of a conventional one
351
the aeroplane monitor on the artificial horizon is fitted to the
instrument case
352
aircraft altitude exceeds cabin altitude and the mach meter has a leak in the static line within a pressurised cabin location this will cause it to
under read
353
the aircraft heading is 270 degrees the magnetic compass deviation is -1degree the pilot should fly
271 degrees
354
the ADC inputs to
altimeter, FMC, secondary radar
355
the aneroid capsule in an altimeter
expands at high altitudes
356
the apparent wander for directional gyros is
compensated by applying a constant torqure
357
the applied pressure to an ASI varies with the
square of speed
358
The ASI fluctuates in reading that means there is
to much pitot on the head
359
the atmosphere is
approx 1/5 oxygen
4/5 nitrogen
360
the capacitance fuel contents system works on the principle of
capacitance
361
the capsule for an ASI will be expanding when the aircraft is
accelerating
362
the capsule in a VSI will be expanded when the aircraft is
depending
363
the capsule in an altimeter responds to
absolute pressure
364
the colour indicated on a EGPWS display when the aircraft is 60 seconds from impact with terrain is
solid amber
365
the command bars in a flight director system indicate
the required path with respect to actual path
366
the compact mode in a EICAS is used
to show maintenance pages and when one display is inactive
367
the compensator in a fuel tank measues
K value of fuel
368
the compensator tank unit in a fuel system adjusts fuel readings for
permittivity
369
the correction for a positive error for coefficient A in a compass
is to rotate clockwise
370
the CX & CT rotors of a control synchro are 90 degrees shifted the output is
zero
371
the deflection of the ADI command bars when flying a localiser approach is proportional to
the difference between the amplitudes on the two modulations
372
the directional gyro is checked every 15 mins for
drift
373
the distance read out on an HSI is
from the DME system
374
the electrical artificial horizon has a movement of
360 in roll and 85 in pitch
375
the electrical output from a remote gyro to an attitude director indicator is
by a control synchro
376
the electrolyte switches used in a gyro system rely upon
change in resistance to operate
377
the erection system on a directional gyroscope had
a switch on the inner gimbal controlling a motor on the outer gimbal
378
the fast erection push button on an electrical gyro horizon must bot be used for a set period after switching on because
excessive hunting will take place
379
the flight recorder accelerometer used in the DFDR system measures vertical acceleration as on of its parameters to values between
plus 6 g to minus 3 g with a null output of one point eight volts plus or minus twenty five millivolts dc
380
the fluid suitable for use in a dead weight tester is
castor-oil
381
the flux detector element
gives heading with respect to magnetic north
382
the four display modes used by the ECAM system are
flight phase advisory failure related manual
383
the frequency of emissions from an under water location device is
37.5kHz
384
the fill testing of a FDR system is accomplished by
real time monitoring of system with ground test equipment
385
the glideslope indicator needle is
horizontal
386
the GPWS in mode 4 would use which inputs to issue a warning
a low range rad alt & configuration of aircraft
387
the hot junction of a thermocouple is
aft of combustion chamber
388
the HSI compass card is positioned by
compass sytem
389
the HSI indicates
heading and course
390
the HIS provides information on
VOR plan map ILS radar
391
the instantaneous VSI is designed to
overcome the inherent lag by utilising and accelerometer
392
the instrument supplied with pitot and if affected by altitude is a
mach meter
393
the loss of the vertical gyro signal to the flight director system would cause
aircraft to overbank
394
the lubber line on a directional gyro is used to
represent the nose of the aircraft
395
the magnets in a compass corrector micro adjuster are
adjustable to obtain the neutral position
396
the manual VOR input is for
the course deviation bar
397
the manufacturer of a pitot head gave a spec indicating 2 inches diameter this the
external dialogue of pitot head
398
the maximum altitude loss permitted during an unpressurised aircraft instrument static pressure system integrity check is
100 feet in 1 minute
399
the maximum deviation on a standby magnetic compass must not be more than
3 degree
400
the millibar is a unit of
barometric pressure
401
the moving element of a radiometer has
two coils
402
the needle of a resolver is connected to
two coils only
403
the nickel-chrome wire resistance varies directly with its temp. at the low end temp the bulb resistance is approx ____ohms and at its high end
200ohm
404
the null seeking AOA probe incorporates
a moving paddle which operates a potentiometer
405
the operation of the AOA indicator us used to detect airflow direction relative to
the longitudinal axis of the aircraft
406
the outputt from a piezoelectric engine vibration transducer us filtered to remove
both very low frequencies and high frequencies
407
the pitch torque motor of an electrically operated gyro horizon reacts between the
instrument case and the outer gimbal ring
408
the pitch bank erection system us used in an electrical gyro horizon to
prevent the pitch switch giving a false indication due to centrifugal effects during a turn
409
the pitot head is fitted on the aircraft the alignment of a pitot head is carried out with
an inclonometer
410
the pointer of a rate of turn indicator will move to the left whenever the aircraft
turns to the left
411
the port and starboard static vents on an aircraft are inter-connected to
cancel errors caused in the static system when the aircraft yaws
412
the rate of precession of a gyro is
inversely proportional to speed and directly proportional to torque
413
the rate of turn information from a turn coordinator is
more instantaneous
414
the result of the equation (DEV E - DEV W)/2 is known as
coefficient B
415
the rigging of a non magnetic pro sensor requires
checking the target clearance in the near position against reference figures
416
the roll motor on a vertical gyro is located on the
lateral axis
417
the runway heading is
QFU
418
the scratch pad in an FMS CDU occupies
first 12 character spaces of the bottom line
419
the sensing element of the flux valve
remains in the same position attached to the aircraft structure
420
the slip indicator on a conventional mechanical gauge layout is combined with the
turn rate indicator
421
the slip indicator on an EFIS system is
indicated electronically on the PFD
422
the speed of a vacuum driven gyro horizon rotor is approx
15000 rpm
423
the speed of the rotor in a turn and slip indicator is approx
4200 rpm
424
the supply of design indicating system
is direct current
425
the supply to an ASI
are pitot and static pressure
426
the temp compensation device in an altimeter is for the
elasticity in capsule material
427
the temperature of boiling water at standard pressure on the F and C scale is
212 & 100 degrees
428
the term alpha angle relates to which system
angle of attack system
429
the to/from indicator on an HSI informs the pilot of which direction he is tracking relative to
a VOR station
430
The TAS output from a CADC will be determined by information fed from
The mach unit & temp sensor
431
the turn and slip indicator employs
a rate gyro
432
the type of gyro used in a gyro compass is a
directional gyro
433
the units of vibration are measured in
relative amplitude
434
the units on the calibrated scale of a VSI are expressed in
100's FT/M (light aircraft)
1000's FT/M (large aircraft)
435
the vane of a stall warning system with a flapper switch is activated by the cahnge of the
stagnation point
436
the Venturi tubes in a vacuum instrument are measured in
inches of mercury
437
the vocal repeition for mode 6 warnings are repeated
twice only
438
there is an airbuble in the compass
it is due to high altitude
439
thermocouple cimbination mostly used for EGT indications are
chrome / alumel
440
to convert degrees C to degrees K
add 273 degrees
441
TO ensure the compass is servicable before installation you would carry out
damping and pivot friction check
442
to fill a dead weight tester
screw out hand wheel and fill reservoir
443
to get the maximum effect from a compass micro adjuster set them
at 90 degree to each others
444
to provvide a linear scale on an ASI a
ranging bar and screws are fitted
445
to return a RVSM compliant aircraft back to flight condition it would be neccassry to
carry out a full test using a calibrated pitot/static test equipment
446
track altitude in a rad alt system begins at
2500ft rad alt
447
TAS computed from IAS takes into account
Temperature and altitude
448
TAS in an ADC is a function of
mach number and temp
449
TAS is IAS corrected for
altitude
450
two fundamental properties of a gyro are
rigidity and precession
451
using the fast erection switch on a standby horizon prior to the flag clearing may cause
application of large current to the control phase windings causing failure
452
vacuum driven gyros
always have automatic erection
453
vertical gyros are limited to 85 degrees movement in pitch to avoid
gimbal lock
454
vibration levels are indicated to the flight crew in
relative amplitude
455
vibration monitoring signals are sent
via a signal conditioner to the gauge
456
vibration pick offs on a high bypass engine are located at the
fan and turbine casing
457
vibration sensore on a modern AVM system are
piezoelectric devices
458
warning indications are produced by the q
central warning computer
459
warnings, cautions and advisories on a CWS are defined as follows
warning the systems condition is critical and requires immediate attention
caution - the system requires timely attention or may do so in the future
advisory - a system is in use or ready for operation
460
water contamination in a capactinace fuel system will cause the
contents to over read
461
what aircraft system supplies power to the standby artificial horizon
battery bus
462
what altitude relative to sea level does the pressure in the standard atmosphere halve?
18000 ft
463
what are the primary colours for use in CRT displays
red blue green
464
what colour is mode 5 alert
amber
465
what colour is the auto land indication lights next to the pilots instruments with excess deviation
red
466
what could cause fluctuations in instruments
water in static line
467
what deviation is indicated by 2 dots on a VOR system
10 degrees
468
what device controls the position of the bearing pointer of a HSI indicator
radio navigation receiver
469
what device is commonly used in mechanical altimeters to compensate for changes in temp
bi metallic u shaped bracket
470
what device is used on the loop antenna to prevent 180 degree ambiguity
sense antenna
471
what does piezoelectric type vinration sensor detect
pressure changes
472
what does a TCAS TA look like
yellow circle
473
what does a vibration type sensor measure
frequency of deflections
474
what effect own the rate of precession will a change of gyro rotor speed have
increase the rotor speed decrease the rate of precision
475
what errors are direct reading compasses subject to
acceleration and turning errors
476
what happens to the F/D command bars if the roll gyro fails in a turn
they disappear out of view
477
what inhibits the GPWS warnings
stall warning system
478
what instrument connects to pitot pressure
the ASI
479
what instrument uses ram air pressure and atmospheric pressure
ASI
480
what is a characteristic of a direct reading compass instrument light wiring
it must be shielded or twisted wire pair
481
what is a characteristic of a HSI compass card
it provides an indication of gyro stabilised magnetic heading
482
what is a precaution relvant to handling gyroscopes
all gyroscope instruments must be stored on at least 100mm of foam rubber
483
what is apparent drift due to
earths rotation
484
what is incorporated in a direct compasses to allow foir damping fluid volumetric changes resulting from temp variation
beloows or a corrugated diaphragm
485
what is inside an aneroid capsule
vacuum
486
what is a lapse rate
temp changes with altitude
487
what is QDR
magnetic bearing from a station
488
what is sqaure law correction applicable to
ASI
489
what is the aural warning of an aircraft over speed
clacking sound
490
what is the calibration law of a radiometer
material of the sensing element
491
what is the error in the lubber line called
index error
492
what is the maximum rad alt track altitude
2500ft
493
what is the maximum value of insulation tester that may be usied in a fuel contents system
250v
494
what is the minimum RVSM seperation
300m
495
what is priomary sensing function element of a direct reading compass
a permanent magnet
496
what is the primary sensor of a slip and skid indicator
a ball in a liquid filled glass tube
497
what is the purpose of a direct reading compass
it provides an indication of aircraft heading with respect to magnetic north
498
what is the purpose of a rate of turn indicator
it provides the pilot with a reference to perform a standard rate turn
499
what is the purpose of a slip and skid indicator
it provides the pilots with indications to enable them to perform coordinated turns
500
what is the purpose of the bimetallic striop in the altimeter
corrects for capsule elasticity
501
what is the spped of an ARINC 429 system
100KHZw
502
what is the typical aircraft hydraulic system pressure
3000psi
503
what kind of gyro is a rate gyro
tied down
504
what moves the aircraft symbol on a HSI or ADI
it doesnt move
505
what must you know when carryiung out a test on a capacticane fuel quantity system
it the probes are wet or dry
506
what parameter is displayed by an ASI
IAS
507
hat prevents an aneroid capsule from collapsijng on itself
a leaf spring
508
whart should you be cautious about when touching pitot tubes
they can be hot
509
what type of gyro is incorporated in a rate of turn indicator
rate gyro
510
what type of gyro is housed within an attitude indicator
displacement gyro
511
what type of pressure sensing device is incorparated in an ASI
differential capsule
512
what will jhappen with a flux valve in a turn
it moves as the aircraft moves
513
what woiuld you connect a quadrantal error corrector to
loop antenna
514
when a compass is in the slave mode
azimuth gyro will be corrected by long term monitoring of the flux valve
515
when a force is applied to a horizontal gyro the precession of thge rotor will continue untill
plane of rotation is in line Wirth the plane of the applied force
516
when a rad alt reaches 2500ft what happens to the display
rad alt foes out of viewwh
517
en a standby compass is replaced on installartion the compensator magnets should be set to
the neutral setting on the new unit
518
when an aircraft is aligned for a compass swing checm to be carried out it will be aligned with an error of plus of minus
5 degree
519
when an aircraft is descending the pressure in the altimeter case
will cause the aneroid capsule to contract
520
when calibrating an electronic fuel capacitance indication system what piece of test equipment would you use
a bridge
521
when carry out a leak test on a pitot/static system
pressure is applied to the pitot system
522
when carry out a pressure leak test on an altimeter you are checking for leaks in the
instrument case
523
when changing a windscreen panel which has a standby magnetic compass located in the vicinity
precautions must be taken ro ensure that the attachment bolts are of the specified type
524
when checking a sensitive altimeter on a pre-flight inspection
the ambient air pressure is set on the millibar scale
525
when more than one D.R compass is fitted on an aircraft or where a DR compass serves as a standby to a remote reading compass
all readings and adjustments for each compass should be made simultaneously on each heading
526
when performing maintenance operations on an aircraft equipped with RVSM system and a quick release disconnect connetion ius disturbed
a full test of the system should be carried out only if the manufacturer recomends to do so
527
when power is switched off the gimbal brake
restricts outer gimbal
528
when refuelling as the fuel level increases
capacticance increases
529
when servicing an RVSM aircraft
the alt alert must be serviceable
530
when testing using a thermocouple test
a serviceable battery is required
531
when the busy indicator lamp flashes on the QAR in a DFDR system this indicates that the
data is being recieved and the cartridge cannot be ejected
532
when the roll torque motor of a vertical gyro attitude ref unit is energised it applies a corrective torque that reacts around the gyro
lateral axis
533
when using a magnetic compass the magnet should be aligned to
the magnetic centre
534
where do you adjust the component Q coefficient C
Coefficient C
535
where does the bimetallic temp strip act in an altimeter
directly on the capsule
536
where does the HSI receive GND speed information from
INS
537
where is aloha angle used
AOA
538
whwere is RNAV directional command info displayed
HSI
539
where is the attitude director stator situated
inside the rotor
540
where is the placment of a mercury switch
outer gimbal
541
where is the sinus.rundown brake on a gyro
outer gimbal
542
which Q code is applied to an altimeter too make it read the airfield height above sea level
QNH
543
which Q code is applied to an altimeter with the aircraft on the ground to make it read the airfield height above sea level
QNHw
544
which activates at the lower speed
stick pusher
545
which axis does the directional gyro spin on
horizontal
546
which GPWS warnings can be disabled if the pilot decided to silence the warning
mode 5
547
which instrument are you most likelty to damage if you have a rapid drop in pressure whilst carrying pitot static leak checks
VSI
548
which instruments shows DH
ADI
549
which is not displayed on an ADI
VOR lateral deviation
550
which is used for compass damping fluid compensation
bellows or diaphragm
551
which metal is used for temp compensation in pressure instruments
invar
552
which modes of the GPWS may be inhibited
modes 4b and 5
553
which of following is a direct reading pressure gauge
standby barometric altimeter
554
which of the following woild cause a displacement gyro to topple
running the gyro at low speed
555
which of these barometric instruments uses a restrictor to compute its output
VSI
556
which of these measuring elemetns is used to measure atmospheric pressure
aneroid capsule
557
which pitot probe provides information to the captains instruments
upper
558
which sensing element is incorporated in a barometric altimeter
static pressure only
559
which warning mode of the GPWS privides a audio warning only
MODE 6
560
while carrying out a leak check of the altimeter if the static is leaking the VSI would
indicate descent
561
why are DR compass card mounted pendulously
to minimise the effects of magentic dip
562
with a constant torque applied to a gyro scope the rate of precision will
decrease with a higher rotor speed
563
with a VSI pointer art position 1 on the upper half of the scale it indicates
1000ft/m rate of climb
564
with airspeed hold engaged whilst flying with flight director engaged a down command means your speed has
decreased
565
with an aircraft on the ground and QNH set on the millibar scale of the altimeter the altimeter will read
the airfield height
566
with an aircraft which has moire than one compass system
master adjusted slave adjusted each having a corrected compass card
567
with engine stopped engine blanks fitted EPR indicator reads slightly above 1
you would adjust the gauge
568
with the gyro at normal running speed a torque applied to the inner gimbal ring of a vertical gyro will cause the
outer ring to move
569
WXR ground clutter suppression uses a discriminator circuit and
anything above .75m/s is ground cloud
570
