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Questions with AnswerInstruments, Magnetism and Compasses

1) Given: pressure altitude 8000ft, QNH altitude 7500ft, OAT +30 degrees C, terrain elevation 5700ft. the approximate altitude above ground is?

2650ft

2) Given: pressure altitude 11000ft, QNH altitude 9500ft, OAT -15 degrees C, terrain elevation 8300ft, the approximate altitude above ground is?

900ft

3) During a stabilized climbing turn at a constant rate of turn, the instruments which indicate the correct pitch and bank are the

Attitude indicator and the turn and slip indicator

4) The instruments, as well as the attitude indicator, which are pitch instruments are

Altimeter, airspeed indicator and vertical speed indicator

5) The instruments which are grouped as pitch instruments are attitude indicator

Altimeter, ASI and VSI

6) The instrument which provides the most pertinent information (primary) for pitch control in straight and level flight is the

Attitude indicator

7) A practical test which should be made on electric tyro instruments prior to engine start is

Turn on the electrical power and listen for any unusual or irregular mechanical noise

8) If the Pitot tube and outside static vent or ports were clogged, the instrument or instruments which would be affected are the

Altimeter, VSI and ASI which would provide inaccurate readings

9) If both the ram air input and drain hole of the pitot system are blocked, the airspeed indicator which can be expected is

No variation of indicated airspeed in level flight even if large power changes are made

10) If the ASI ram air input and drain hole are blocked a pilot can expect that

The airspeed indicator will react as an altimeter

11) If the static pressure ports iced over while descending from altitude, the ASI would read

High

12) If the pitot opening is clogged by ice or dirt or the pitot cover is left on, the instrument(s) which will be affected (separate static source) are

ASI only

13) If the ram air input to the pitot head of the pitot system becomes blocked (drain hole open), the indicated airspeed will generally

drop to zero

14) The location of the static vent which would provide the best measurement of static pressure under variable flight conditions is one installed?

On each side of the aircraft where the system will compensate for variation or aircraftaltitude

15) The effect on the instrument indications when using the alternate static source of static pressure (which is vented inside an unpressurised aircraft) is that

The altimeter may indicate higher than the actual altitude being flown

16) If the static pressure tubes are broken inside a pressurized cabin during a high altitude flight, the altimeter would probably indicate

Lower than actual flight altitude

17) If while in level flight, it becomes necessary to use an alternate source of static pressure vented inside the aircraft, the variations in instrument indications which the pilot should expect are

The altimeter will read higher than normal, airspeed will not change and the VSI will momentarily show a climb.

18) When a pitot tube is clogged, the instrument which would be affected is the

ASI

19) The pitot system provides impact pressure only for the

Airspeed indicator

20) Pitot static system errors are generally the greatest at

High airspeed

21) As an aircraft is rolled out of a left 180 turn to straight and level flight on the attitude indicator, the aircraft will be in slight

Turn to the right a climbing slightly

22) The approximate point in a normal co-ordinated turn when the turn error in a vacuum driven attitude indicator is at a maximum is

180 degrees of turn

23) Errors in both pitch and bank indication on an attitude indicator are usually at a maximum as the aircraft rolls out of a

180 degree turn

24) If a suction gauge indicates that the pressure is lower than the minimum limit, the air operated instruments which would be affected are

Heading indicator

25) The instrument which would be affected by low pressure as indicated on the suction gauge is the

Heading indicator

26) When an aircraft is decelerated some attitude indicators will precess and incorrectly indicate

A descent

27) One characteristic which a properly functioning gyroscope depends upon for operation is

Resistance to deflection of the spinning wheel or disc

28) During deceleration of an aircraft some attitude indicators will precess and falsely indicate

A decrease in pitch attitude

29) When an aircraft is rapidly accelerated in straight and level flight, such as take off, the inherent precession characteristic, if any, which will be displayed on the attitude indicator is

The miniature aircraft would indicate a climb

30) Acceleration error will be displayed on the attitude indicator by a false

Nose high indication

31) When an aircraft accelerates, some attitude indicators will precess and incorrectly indicate a

Climb

32) Aircraft deceleration (suction driven attitude indicator) may cause the attitude indicator to indicate a

Bank to the left – nose low attitude

33) When considering the effect of temperature changes on the indication s of a sensitive altimeter it is true to say that

Colder than standard temperatures will place the aircraft lower than the altimeter indicates

34) When ambient temperature is warmer than standard temperature at a particular altitude, the altimeter will indicate

Lower than true altitude

35) For a given indicated airspeed, a high density altitude will always result in

An increase in true airspeed

36) An increase in density altitude will mean an increase in

TAS

37) Pressure altitude is the altitude

Referenced to the standard datum plane

38) The pressure altitude at a given location is indicated by the altimeter after it is set to

1013.2 hPa

39) To determine pressure altitude before take off, set the altimeter to

1013.2 hPa and the altimeter indication noted

40) The reported altimeter setting of a given station is the

1013.2 hPa and the altimeter indication noted

41) The reported altimeter setting of a given station is the

Station barometric pressure corrected to mean sea level pressure

42) An altimeter is set to 1010.9 hPa and the correct altimeter is 1016.1 hPa. If under these conditions a landing is made at an airport where the airfield elevation is 772ft, the altimeter would indicate approximately

613ft

43) En route at FL270, the altimeter is set correctly. On descent, the pilot fails to reset to the local altimeter setting of 1026.1 hPa. If the field elevation is 1300ft and the altimeter is operating properly, the indication after landing is

913ft

44) En route at FL250 the altimeter is set correctly. On descent the pilot fails to reset the local altimeter setting of 1037.8 hPa. If the field elevation is 650ft and the altimeter is operating properly, the indication after landing is

-88ft

45) Flying into a colder air mass and while maintaining a constant pressure altitude and CAS, the effect will be a

Lower TAS and a lower true altitude

46) If flight made from an area of high pressure into an area of lower pressure without the altimeter setting being adjusted. If a constant indicated altitude is maintained, the altimeter would?

Be lower than indicated

47) A flight is made from an area of high pressure into an area of lower pressure without the altimeter setting being adjusted. If a constant indicated altitude is maintained, the altimeter would?

Higher than the actual altitude above sea level

48) True altitude will be lower than indicated altitude for an altimeter setting of 1013.2 hPa even with an accurate altimeter

In colder than standard air temperature

49) True altitude is

Actual height above sea level corrected for all errors

50) If an altimeter indicates 3500 ft amsl with an altimeter setting of 1004.7 hPa the approximate pressure altitude is

3745 ft

51) If an altimeter indicates 2500 amsl with an altimeter setting of 1026 hPa the approximate pressure altitude is

2110ft

52) An altimeter of an aircraft on the apron will indicate lower than the actual elevation with a

Atmospheric pressure increase

53) A pilot parks an aircraft with the altimeter indicating the correct elevation. The atmospheric change which will cause the altimeter to indicate lower than the actual elevation is an increase

In atmospheric pressure

54) Given indicated altitude 7000ft, OAT +20 degrees C, pressure altitude 7000ft, the true altitude is

7475ft

55) If while on the ground, a sensitive altimeter is set to 1013 hPa and the ambient pressure is 1013 hPa, the altimeter will indicate

Field elevation

56) Regarding vertical speed indicators it is true to say that

A lag of 6-9 seconds is required to stabilize pressure within the instrument

57) Regarding the vertical speed indicator, it is true to say that

A lag of 6-9 seconds occurs before pressure within the instrument stabilizes

58) Prior to engine start, the turn and slip indicator should be checked to determine if the

Needle is approximately entered and the tube is full of liquid

59) If a standard rate turn is maintained the time required to turn clockwise from heading of 090 degrees to a heading of 180 degrees is

30 seconds

60) In a coordinated turn the displacement of the turn needle

Increases as the angle of bank increases and the airspeed decreases

61) The indications from the turn and slip indicator during taxi should be

The ball moves freely opposite the turn and the needle deflects in the direction of the turn

62) If the outside air temperature increases during a flight at constant power and at a constant indicated altitude, the true air speed will

Increase and true altitude will increase

63) True airspeed determined by correcting

RAS for density altitude error

64) Regarding the relationship of true airspeed and indicated airspeed as altitude increases, it is true to say that

For a given true airspeed, indicated airspeed decreases

65) If a pilot plans to land at an airport where the elevation is 7500ft the indicated approach speed should be

The same as that used at a sea level airport

66) When comparing IAS for take off from high elevation airports with IAS for takes off from lower elevation airports, the correct IAS to use is

The same at all airport elevations

67) The highest indicated airspeed will be obtained during level flight at a constant power setting when the outside air is

Cold and dry

68) An aircraft is at a constant power setting with constant indicated altitude. As a result of a decrease in the outside air temperature, the true airspeed will

Decrease and the true altitude will decrease

69) An aircraft is descending at a constant Mach 0.6. The true airspeed will

Increase as temperature increases

70) Rectified airspeed is

Indicated airspeed corrected for instrument and installation error

71) While in a shallow turn, the magnetic compass card

Remains stationary and the aircraft rotates around the compass card

72) Regarding the magnetic compass, it is true to say that

As speed decreases on a westerly heading the aircraft will indicate a turn to the north


If on a westerly heading and speed is decreased, the compass will indicate a turn to the north

74) Deviation is

Magnetic disturbances within an aircraft that deflect the magnetic compass


Magnetic dip increases with an increase in latitude

76) It is true to say about magnetic deviation of a compass that

Deviation varies for different headings of the same aircraft

77) Magnetic compass deviation is caused by

Magnetic attractions in the aircraft

78) The deviation error of a magnetic compass varies with the

Aircraft electrical systems in use

79) Deviation in a magnetic compass is caused by

Magnetic fields within the aircraft distorting the lines of magnetic force

80) The compensating magnets of a magnetic compass should be adjusted

With the engine running

81) On the taxi check, the magnetic compass should

Swing freely and indicate known headings

82) The term drift refers to the wander of the axis of a gyro rotor in

The horizontal plane only

83) The three variables in the earth’s magnetic field are

Variation, intensity and angle of dip

84) A line of zero variation is called

An agonic line

85) A magnetic material which is easily magnetized is called

Soft iron magnetic material

86) at a latitude of approximately 45 degrees

Both z and h are average

87) Compass accuracy is greatest

At the magnetic equator

88) Parameter P is

Fore and aft magnetism affecting coefficient B

89) If the static source to an altimeter becomes blocked during descent, the instrument will

Progressively under read

90) Dev on north – Dev on south = 2

Coefficient C

91) The secular change in variation has a cycle of

960 years

92) On a 1:1000 000 chart it states that lines of equal magnetic variation are drawn for 1978 (annual change 8 degrees eastwards). The 21 degrees W signal is now equal to

20W

93) An aircraft made in South Africa has a red pole in the nose and right wing and blue poles in the tail and left wing. The heading during construction was

315 degrees

94) The component of aircraft magnetism along the athwart ships axis is

Component Q

For questions 95 to 103 use the following swing details

Correcting Swing Check Swing

Landing compass Aircraft compass Landing compass Aircraft Compass

003 359 316 317

085 091 358 000

170 178 042 042

265 267 089 093

134 135

177 179

110 223

269 272

95) Coefficient C is

+6

96) After correction for coefficient C, the compass should read

172

97) Coefficient B is

-2

98) After correction for coefficient B the compass card will read

269

99) Coefficient A is

-2

100) If coefficient A is corrected while standing on Compass heading 317, the compass reading after correction will be

315

101) When making out the deviation card, the note against the heading of 045 is

Steer 043

102) The residual deviation on heading 180 would be

0

103) On a deviation card for heading (M) 225 should be written

Steer 225

104) Corrections for coefficient A assume that the error is

Apparent Coefficient A

The following readings were observed during the swing of a direct reading compass. Use this information for questions 105 to 111.

Magnetic Heading Compass Heading

004 001

047 045

088 091

130 134

176 181

224 226

270 271

317 315

10) Coefficient A would be

-1

106) Coefficient C would be

+4

107) If C were corrected on a compass heading of 181, the compass should read

177

108) Coefficient B would be

-1

109) If coefficient B were corrected on a compass heading of 271, the compass should read

272

110) If coefficient A were corrected on heading 270, the compass should be made read

269

111) On the deviation card against ‘for 225’ should be written

Steer 224

112) A direct reading compass has the following coefficients

A= -1, B= -6, C= +4 on a magnetic heading of 000 the compass will read

357

113) Using the same coefficients as in question 111 the deviation on a magnetic heading of 045 would be

-2.4

114) Using the same coefficients as in question 111 the deviation on a magnetic heading of 313 would be

+6

115) The wing tip detector unit has degrees of freedom of

25 degreed pitch and roll, nil in azimuth

116) When turning from east to south in the s hemisphere you should

Roll out on 160 degrees

117) Acceleration errors to the compass occur

On easterly and westerly headings

118) The stator rotor in a remote reading compass is on the same shaft as

The vertical bevel gear and the gyro unit pointer

119) Coefficient –B has the blue pole

In the tail

120) Ideally, compass liquid should have the following properties

Low viscosity

121) The gyro selection of the remote reading compass would be used

Near the Poles

122) The part of the remote reading compass which senses magnetic heading is called

The flux valve

123) The type of compass least likely to suffer from parallax is a

Remote reading compass

124) Hard iron magnetism is the same as

Permanent magnetism

125) When a magnet cannot be made magnetic any more it is said to be

Saturated

126) A compass magnet would normally be made of

Hard iron

127) It is true to say that

The earth’s South Pole is red and Z is maximum

128) The magnetic equator is the same as

An aclinic line

129) A blue pole in the left wing would cause

- Q component

130) Referring to question 129, the resulting coefficient would be

C

The following figures apply to the swinging of a compass. Use them to answer questions 131 to 144.

CORRECTING SWING CHECK SWING

Landing compass, Aircraft Compass, Landing Compass, Aircraft Compass, Deviation

184 183 134 129 +5

272 268 181 177 +4

000 353 225 222 +3

088 088 272 270 +2

314 308 +6

357 353 +4

048 044 +4

094 091 +3

131) The value of coefficient C would be

+3

132) If you corrected coefficient C on heading 183, you would make the compass read

180

133) The value of coefficient B would be

-2

134) If correcting for coefficient B on 268, you would make the compass read

270

135) The original deviation on west was

+4

136) After correction for coefficient B the deviation on west is

+2

137) The original deviation on north was

+7

138) After the removal of coefficient C the residual deviation on north is

+4

139) After the check swing the value of coefficient A is

+4

140) When correcting for coefficient A on heading 091, you should make the compass read

095

141) After completing all corrections, the residual deviation on 225 would be

-1

142) The residual deviation on a compass heading of 045 would be

0

143) On your deviation card for south you would write ‘steer….’

180

144) On the deviation card for 315 you would write ‘steer….’

313

145) The term CAS has the same significance as

RAS

146) You are flying at 20 000ft at an IAS of 150kts. The static tube is blocked as you start descent. You would expect the IAS to

Indicate +/- 170kts

147) Compressibility correction is usually applied at speeds

Over 300kts

148) The correction for compressibility gives

CAS

149) Altimeter setting which gives height above airfield level is

QFE

150) Regional QNH is

The lowest QNH which can be expected in the region

151) The airfield is 5000ft amsl. The QNH is 990hPa. The QNE would be

5696

152) QNH is 1007.2hPa and you are flying at FL055 over high ground 3850ft amsl. Your clearance above the high ground is

1452

153) An aerodrome 990ft amsl has a QFE of 990hPa. The QNH is

1023

154) Flight level 170, OAT +10 degrees C, QNH altitude 16 500ft. true altitude is

18 500ft

155) An aircraft on track 189 degrees M wishes to fly at the lowest level which will give a clearance of 5 000ft amsl. If the regional QNH is 992hPa, the flight level is

FL060

156) An aircraft is at FL065 and the QNH is 1003hPa. There is high ground at 1350m amsl. The actual absolute altitude of the aircraft over the high ground is

1772ft

157) The pressure instrument which does not suffer from instrument error is

VSI

158) In the servo altimeter

The capsules drive the I bar

159) The capsule movement of an ordinary altimeter would be least at

30 000ft

160) The effect of a blocked static line in a pressurized aircraft cruising at FL150 would be

Altimeter stationary, VSI zero

161) In the VSI

Delayed static is in the case and static in the capsule

162) The speed of sound varies as the square root of

Absolute temperature

163) The directive force on a compass needle is

H

164) The effect of dip is counteracted by

Low CG

165) It is correct to say that

Coefficient B is caused by parameter P acting fore and aft

166) If you would fly an aircraft from the s hemisphere to the n hemisphere you would expect

Changes in both drift rate and deviation

167) When you deflect a compass needle 10 degreed either side and check that it settles within 2 degrees each time you are checking

Pivot friction

168) The advantages of the remote reading compass are

Turning errors eliminated, permits multiple presentation of heading

169) In the remote reading compass the earth’s magnetic flux is sensed by

Secondary coil

The following details of headings obtained during a compass swing are to be used for questions 170 to 182.

Aircraft Compass Landing Compass

000 003

046 044

090 084

134 129

179 174

227 223

270 270

315 319

170) the value of coefficient C is

+4

171) if coefficient C is adjusted on heading 179 you would make the compass read

183

172) to make the adjustment you would

Place the key in the athwart ships hole of the micro adjuster

173) coefficient B would be

-3

174) to correct for coefficient B on heading 270, you would make the compass read

273

175) the value of coefficient A is

-2

176) to correct for coefficient A on heading 315, you would make the compass read

313

177) to make the correction in question 175, you would have to

Turn the bowl anti-clockwise

178) after correction for coefficients A, B and C the residual deviation on north would be

+1

179) after the same correction the residual deviation on 315 would be

+1

180) on a magnetic heading of 135 the compass would read

134

181) on a compass deviation card for east you would write

Steer 091

182) on a magnetic heading 225 you would write on the card

Steer 226

183) if coefficient A is -1, coefficient B is +2 and coefficient C is -2, the deviation on heading 315 is

-3.8

184) if coefficient B is +7 and coefficient C is -6, the deviation on heading 200 is

+3.25

185) assuming the compass is only affected by hard iron magnetism causing deviation, if the latitude changed the deviation would change because of the change in the

Strength of the earth directive force

186) if you were making a turn in the s hemisphere from south-west to the right on to north you should come out of the turn on

020

187) acceleration errors are caused because

The CG lies between the pivot and the equator

188) in the remote reading compass, the slow corrective rate of the tyro means that it is necessary to align the unit by means of

The synchronizer

189) you are passing over a spot height of 1 600m amsl with a regional QNH of 996hPa FL70. The actual clearance over the spot height is

1 206ft

190) you take off from Umtata (2 400ft amsl) with QNH 1020hPa set and fly to Port Elizabeth (225ft amsl) at FL 080. Arriving at PE you are unable to obtain a QNH and decide to fly at 1500ft on QNH 1020hPa. The actual height agl if the real QNH at PE is 990hPa is

375ft

191) using the same details as in question 189, QNE at Port Elizabeth is

915ft

192) in the servo altimeter the servo motor drives

The counters and cam

193) an altitude alerting device can be incorporated in

A servo altimeter

194) after setting QNH at an airfield at 5 000ft amsl, you would expect the altimeter to read within

+/- 80ft

195) if the altimeter is 150ft high when you check airfield height against QNH you would

Cancel the flight until the altimeter is serviceable

196) the barometric pressure at aerodrome level reduced to sea level using the ISA formula is

QNH

197) cruising at FL200 in a pressurized aircraft with the cabin at 5 000ft, the pitot line in the cabin breaks. You would expect

The ASI to be inaccurate, VSI to read zero and altimeter to read 20 000

198) in considering ASI errors, RAS plus density correction gives

TAS

199) an unusual feature of the VSI compared with other pressure instruments is

That it does not have static pressure in the case

200) the vertical speed indicator has

A logarithmic scale

201) the purpose of the scale on the dial of a VSI is to

Give better accuracy at the lower rates of climb

202) what is the function of the two capsules in the Mach meter

It solves the equation Mn = TAS/LSS

203) at flight level 330 in standard conditions the speed of sound is

579kts

204) in the same conditions as in question 202, Mach 0.84 represents a speed of

485kts

205) the gyroscopic property of rigidity is based on Newton’s

First law

206) it is true to say that

The turn and bank rotates at 9 000, the A/H at 15 000, and the DI at 12 000 rpm

207) if pressure within a Bourdon tube is increased it tends to

Straighten

208) the artificial horizon (suction type) has a

Vertical axis

209) in an aircraft flying west in the s hemisphere the DI transport wander is

Negative

210) earth rotation wander at latitude 30ºS is

+7.5º/hr

211) the limits in pitch of the suction driven Artificial Horizon are

+/-60º

212) the gyro instrument which cannot be toppled is

The turn and bank

213) a rate 1º turn means changing heading at

3º/second

214) on direct track 350ºT from FAQT to FABL, the highest ground on track is 6 882ft. mean variation 20 W. minimum safety height is 1 500ft. forecast QNH 1026hPa. The minimum safe lowest IFR flight level assuming 1hPa = 30ft is

FL090

215) in an artificial horizon indicator bank indication is given by an index against a scale. This is controlled by

Movement of the instrument face and scale about the sky plate

216) in flight the normal static port becomes blocked. The alternate static source is selected causing an immediate increased reading on the ASI. The altimeter is dependent on the same standby source with the result that the altimeter reading will

Increase

217) compressibility will make the airspeed indicator

Over read

218) an aircraft is flying at a constant indicated airspeed and constant indicated altitude. As a result of a decrease in the OAT, the TAS and true altitude will

Both decreases

219) the Sperry CL2 compass system remains synchronized in a turn because

The signals from the detector unit to the signal Selwyn change at the same rate as the rotor of the signal Selwyn turns

220) when executing a rate 1 turn onto north in the s hemisphere the aircraft should be rolled out of the turn

Some 25 - 30º after the compass reads north

221) instrument errors in altimeters

Increase with an increase in altitude

222) to check an altimeter for serviceability on the ground at an aerodrome, the altimeter should be set to

QNH and the reading confirmed by comparing with ground elevation

223) the magnetic system of a compass is suspended pendulously to counteract the effect of component

Z

224) with standard pressure set on the sub-scale, indicated altitude will be that same as the true altitude

At sea level under standard conditions

225) the turn and slip indicator utilizes a

Rate gyro

226) an aircraft at FL230, OAT -41ºC, QNH 983hPa, is at a true altitude of

21 112ft

227) in the operation of the turn indicator, a rate gyro is used which has

Complete freedom of movement in two planes, at 90º to each other and is constructed to measure rate of turn in the third plane, at right angles to the other two.

228) assuming the speed of sound is 1 203.8km/hr at 15ºC and the mean lapse rate is 2º/1 000ft, the speed of sound at a temperature of -56.6ºC is

564.2kts

229) the angle of tilt of the rate gyro in a turn indicator is produced by

Secondary precession produced by spring tension balancing primary precession

230) after 4 hrs and 15mins the easterly axis point of a horizontal axis gyro set with its axis in an east /west direction at N45 will have

Drifted clockwise and have risen above the horizon

231) the deviation of a direct reading magnetic compass affected only by coefficients B and C are 8ºE on a heading 230ºC and 4ºW on heading 130ºC. Therefore the deviation on heading 315ºC is

3.3ºE

232) while cruising in IMC the needle of the ASI returns to zero. This is probably because of a

Leak in the capsule

233) in the s hemisphere, a magnetic compass will normally indicate a turn towards south as

A left turn entered from an easterly heading

234) deviation in a magnetic compass is caused by

Magnetic fields within the aircraft distorting the lines of magnetic force

235) prior to starting the engine(s) the turn slip indicator should be checked to ensure the

Needle is approximately centered and the tube is full of liquid

236) an aircraft flies from a high pressure area to a low pressure area. The altimeter (QNH) setting is not altered. At destination the altimeter reading is

Higher than actual altitude

237) during flight the vacuum pump fails. This may result in failure of

The DI, AH and turn indicator of the turn and bank indicator

238) the E2 compass has correctors built in for coefficients

B and C

239) the true altitude for FL100 with a QNH of 1030 and OAT +6º is

10 940ft

240) the pitot system provides dynamic pressure for the

Airspeed indicator

241) the AH, DI and turn indicator have the following properties in common

Rigidity and precession

242) in order to indicate heading, the DGE employs a horizontal axis tyro and utilizes the principle of

Rigidity in space

243) the rigidity of a spinning wheel is directly proportional to

The speed of rotation and inversely proportional to the mass of the rotor.

244) the elevation of aerodrome A is 390ft and aerodrome B 450ft. A pilot at A sets his altimeter to read aerodrome elevation and then flies to B without resetting the altimeter. If aerodrome pressure at an on departure was 1004hPa and at B the altimeter reads 630ft on landing, the QNH is

+/- 998hPa

245) the value of compressibility error of the ASI will

Increase with increase in altitude and true airspeed

246) the required track is 155ºT. Variation is 24W and the deviation card reads ‘for south steer 178’. In no wind the compass heading to steer is

177

247) to convert IAS to RAS, the factors taken into account are

Position error and instrument error

248) the principle used by the VSI to detect rate of change of altitude is

Variations of a capsule fed with ambient static pressure surrounded by delayed static pressure supplied through a metering choke

249) ambient static pressure is fed to the airspeed indicator in flight to

Cancel static pressure entering the instrument diaphragm through the Pitot tube

250) for an aircraft climbing at a constant TAS

The rectified airspeed decreases and the Mach number increases

251) for an aircraft flying at 110 KIAS the approximate angle of bank to maintain a rate 1 turn is

18º

252) including the plane of rotation, a space gyro is defined as having

Three gimbals, freedom of movement in four planes, gyroscopic inertia relative to space

253) the advantage of an electric turn coordinator when the aircraft has a vacuum system for other gyroscopic instruments is that

It provides back up in case of vacuum system failure

254) on an easterly heading overhead Arena Academy, an aircraft is accelerated. The compass indicates

An apparent turn to the south

255) flying into an area of low pressure, the altimeter will

Over read

256) the amount of flux induced into a horizontal Ferro-alloy bar by the earths magnetic field is proportional to the

Strength of the earths directive force and the angle between the bar axis and the local magnetic meridian

257) an ASI functions by moving through the air whereby the

Difference between pitot and static pressure is measured and indicated

258) the altitude in the standard atmosphere at which a TAS of 465kts corresponds to M0.80 is

32 950ft

259) at a constant pressure altitude of 1 250ft, a temperature drop from 29ºC to 18ºC will make the density altitude

Decrease by 1 870ft

260) the altimeter is subject to barometric error which is caused by

Pressure variations from standard calibration conditions

261) to compensate for errors induced by expansion and contraction in the mechanism of the altimeter caused by temperature changes the following system is used

A bimetallic strip is incorporated in the linkage which distorts in a corrective sense according to the temperature

262) the rate of precession of a spinning tyro is directly proportional to

The force applied

263) in a coordinated turn the displacement of the turn needle of a turn and slip indicator

Indicates as the angle of bank increases and the airspeed decreases

264) in the Southern hemisphere, the magnetic compass will indicate

A turn to the north if the aircraft speeds is decreased on a westerly heading

265) the static vent serves the

Airspeed indicator, altimeter and vertical speed indicator

266) an unusual feature about the VSI when compared with other pressure instruments is

That it does not suffer from instrument error

267) if the pitot line in the cabin breaks when cruising at FL200 in a pressurized aircraft with the cabin altitude at 5 000ft, it will cause

The ASI to be inaccurate, VSI to read zero and altimeter to read 20 000ft

268) when an aircraft is flying from a warm air mass into a cold air mass

TAS and true altitude decrease

269) while at a constant RAS and altitude an aircraft flies from a cold air mass into a warm air mass. The mach no will

Remain constant

270) instruments which use pitot pressure are

ASI and Mach meter

271) an aircraft descends from FL310 to FL 040. At FL160 the Pitot tube becomes blocked by ice. At FL120 the ASI would

Under read

272) the errors of an ASI are

Pressure error, instrument error, density error and compressibility error

273) an aircraft flies from cold air to warm air at a constant TAS. RAS would

Decrease

274) an aircraft is to fly a magnetic track of 310º at the lowest safe semi-circular flight level. High ground en-route is 2 250m amsl and a minimum clearance of 3 000ft is required. The regional QNH is 1028hPa. The lowest flight level would be

FL100

275) for an aircraft flying at Mach 0.82 at FL350, OAT -35ºC, the RAS would be

264kts

276) an aircraft flying at Mach 0.78, TAS 479kts in ISA conditions at

FL200

277) an aircraft is at FL330 with the altimeter set correctly. On the descent the pilot fails to set the QNH of 1026.1hPa. Airfield elevation is 1 800ft. the reading on landing is

1 400ft

278) an aircraft departs from A (elevation 240ft) with QFE 993hPa set, en-route to B (360 nm from A) where the QNH is 1019hPa. A spot height of 1 660m amsl 60nm from A is cleared by 1 500ft. the altimeter reading overhead the spot height was

4 470ft

279) airfield elevation 4 000ft, temperature +15ºC, QNH 996hPa. Density altitude is

5 600ft

280) pressure altitude 15 000ft, OAT +20ºC, QNH altitude 15 700ft. true altitude is

17 800ft

281) an aircraft departs A, airfield pressure 984hPa and the altimeter indicates airfield elevation of 1 050ft. the aircraft flies to and lands at B (elevation 2 500ft) where the altimeter reads 2 710ft. the QNH at B is

1012hPa

282) a warning flag appears on an electrical turn and slip indicator. This means

Turn indicator failure – slip indicator serviceable

283) the DGI, Artificial horizon and turn indicators are

Tied, earth and rate gyros respectively

284) the principle of primary precession only is used to control the gyroscopes of the

DGI and AH

285) the principle of rigidity is used by the

DGI and AH

286) with reference to gyroscopes: R = rigidity, P = precession, S = rotor speed, I = moment of inertia, F = external force. The correct formula for rigidity is

R O S I

F

287) the acceleration (take off) error of an air driven artificial horizon is a false indication of

A climbing turn to the right

288) an aircraft compass system has the following coefficients present: A = +1, B = +3, C = -2. The deviation on heading 315ºC is

-2.5º

289) the following figures appear on a compass deviation card

For magnetic Steer Compass

135 134

180 184

290) the required heading is 142ºT and variation is 20ºW. The compass heading is

164ºC

Magnetic heading Compass heading

000 001

090 086

180 180

The coefficients present in the compass system are

A = +2, B = +2, C = -3

291) an aircraft accelerates on heading 270ºC in the s hemisphere. A direct reading magnetic compass would indicate

An apparent turn to the south

292) an aircraft turns left from 045º onto 200ºC in the s hemisphere. The best heading to roll out of the turn would be

220ºC

293) an aircraft compass system has the following coefficients, A = +1, B = -3, C = +2

Deviation on heading 225ºC will be

+1.7ºC

294) the Sperry CL2 compass system does not suffer from turning and acceleration errors because of

The slow precession rate of the gyro

295) an aircraft leaves airfield C (elevation 510ft) with QFE 999hPa set on the altimeter, en-route to Y (510nm from Y) where the QNH is 1025hPa. A spot height (450m amsl) 114nm from X is cleared by 2 000ft. the altimeter reading overhead the spot height was

2 906ft

296) while parked on the apron with elevation 4 060ft, ATC passes a QNH which when applied to the altimeter makes it read 4 140ft. the correct procedure is

Call a technician as the instrument is out of limits

297) according to an aircraft manual, the pressure error correction to be applied to the ASI is +3kts at 100kts. FL100, the VSI will

Read correctly.

298) If the Pitot head and Static Vent were blocked by ice, which instruments would be affected?

Altimeter, VSI and ASI would give inaccurate readings.

299) If the Pitot Head is blocked, that airspeed indication can be expected?

No change of IAS in level flight, even with large power changes.

300) If the static vent became blocked during a descent the IAS would read?

High.

301) If the Pitot opening is blocked, which instrument would be affected (separate static vent)?

ASI only.

302 Rectified Airspeed is?

IAS corrected for instrument and pressure error.

303) An aircraft is maintaining FL120 in cloud. The ASI reading falls to zero. The most probable cause is?

ASI malfunction.

304) An aircraft is flying from a cold air mass into a warm air mass. The TAS and true altitude will?

Both increase.

305) An aircraft flying from warm air to cold air at a constant TAS. The RAS would?

Increase.

306) An aircraft leaves FL 160 for an approach and landing at an airfield. The pilot will set QNH at the?

Transition level.

307) Transition altitude is obtained from?

Jeppesen or Aerad flight guides.

308) Transition level is obtained from?

ATC or VOR ATIS.

309) The location of the static vent which could provide the most accurate measurement of static pressure under variable flight conditions is?

One on each side of the aircraft where the system will compensate for variation of aircraft attitude.

310) Pressure Altitude at an airfield is indicated by an altimeter when the barometric subscale is set to?

1013.25hPa,

311) If while in level flight, it becomes necessary to use an alternate source of static pressure vented inside the aircraft, with the cabin pressure being lower than static, the following variations in instruments indication would be expected?

The altimeter will read higher than normal, airspeed greater than normal and the vertical-speed indicator will momentarily show a climb.

312) Assume that an aeroplane at 17000ft AMSL has a cabin pressure equal to an altitude of 7000ft. if the pilot static tubes break at a point within the cockpit, the altimeter would read?

The cabin pressure altitude, i.e. 7000ft.

313) An aircraft maintains a constant TAS of 350kts in the climb?

LSS decreases and the RAS decreases.

314) An aircraft flying at FL330, Mach 0.82 flies into colder air mass. The TAS will?

Decrease.

315) An aircraft descends from FL410 to FL220 at a constant Mach number. The TAS will?

Increase.

316) Climbing at a constant Mach number, the RAS will?

Decrease.

317) As air density increases, the ASI compressibility error will?

Decrease.

318) An aircraft flies from cold air mass into a warm air mass at a constant FL and RAS. The Mach number will?

Remain constant.

319) If the static vent becomes blocked during a climb the mach meter will?

Under read.

320) Ambient static pressure is fed to the ASI in flight to?

Cancel static pressure entering the instrument diaphragm through the pitot tube.

321) The static vent is blocked. If the glass covering the VSI is broken, the instrument will?

Readings will be reversed.

322) During a pre-flight check the VSI shows 100 ft/min climb. You may?

Have to adjust before flight.

323) The ASI has a pressure error of +5 knots at IAS 130 kts. At the airspeed the VSI would?

Read correctly.

324) The reported QNH of a given station is the?

Station’s barometric pressure corrected to mean sea level pressure.

325) When ambient temperature is warmer than standard at a particular altitude, the altimeter will indicate?

Lower than true altitude.

326) ASI compressibility error will increase with an increase of TAS and?

Increase with altitude.

327) The principle and operation of a Mach meter precludes the following errors?

Temperature, compressibility and pressure errors.

328) The Instantaneous VSI incorporates an accelerometer unit. The pistons of the accelerometer unit are connected?

To the static pressure tube leading to the capsule and their movement creates an immediate pressure change inside the capsule when climb or descent is initiated.

329) In the servo altimeter the servo motor drives the?

Counters and the cams.

330) By changing from QNH to QNE on a servo assisted Altimeter?

The anvil moves, changing the air gaps between the “E” and “I” bars.

331) If the static pressure ports iced over while descending from altitude, the airspeed indicator would read?

High.

332) The rigidity of a spinning wheel is directly proportional to?

The speed of the rotation and indirectly proportional to the mass of the rotor.

333) Errors is both pitch and bank indication on an attitude indicator are usually at a maximum as the aircraft roll out a?

180º turn.

334) When an aircraft is rapidly accelerated in straight and level flight, or at take-off, what inherent precession characteristics will be displayed on the attitude indicator?

The miniature aircraft would indicate a climb and bank.

335) The Turn and Slip indicator pre-flight check consists of?

Aircraft level, turn needle central, ball central, fluid in tube.

336) What indications should you get from the Turn And Slip indicator during taxi?

The ball moves opposite to the turn and the needle deflects in the direction of the turn.

337) The effect of decreasing rotor speed in the turn and slip indicator will cause?

The turn indicator to under-read the rate of turn.

338) The angle of tilt of the rate gyro in a turn indicator is due to?

Primary precession which is generated by an aeroplane rate of turn.

339) To compensate a 360º turn using the Turn Co-coordinator, takes 131 secs. The rotor speed is?

High.

340) The rigidity of a gyro is directly proportional to?

Gyro inertia and rotor speed.

341) If the rotational speed of the Turn and Slip gyro rotor is below the calibrated speed the?

Turn indicator under-reads, slip is not affected.

342) A warning flag appears on an electrical Turn and Slip indicator, this means?

Turn indicator failure. Slip indicator serviceable.

343) The principle of rigidity is used for the operation of the following gyroscopic instruments?

Directional Gyro and Artificial Horizon.

344) An Artificial Horizon employs a?

Earth Gyro.

345) One characteristic that a properly functioning gyro depends upon for operation is the?

Resistance to deflection of the gyro rotor.

346) The Latitude Rider nut of a DGI compensates for?

Earth rotation wander.

347) The Latitude Rider nut of a DGI is set to give zero drift due to the Earth’s rotation at 30ºS. the gyro readings will?

Increase when flying South from 30ºS.

348) The rotor of the DGI spins up and away from the pilot when 090 is indicated. The latitude compensation nut situated on the near right side of the inner gimbal from the gyro axis, has been set to give drift on the ground at the equator. To compensate for earth rotation at 30ºS the latitude compensating nut?

Must be adjusted onwards.

349) What is earth rotation wander at 30º S?

+7.5º per hr.

350) If a vacuum gauge indicates the pressure to be lower than the minimum limit, the air operated instruments that would be affected are?

Heading indicator (DGI).

351) The air driven Artificial Horizon erection error is due to?

Centrifugal Force displacing the vanes.

352) The DGI, Artificial Horizon and Turn indicator are?

Tied, Earth and Rate gyros respectively.

353) Erection errors in an air driven Gyro Horizon Indicator are due to?

The movement of the pendulous vanes during aircraft acceleration or a turn manoeuvres.

354) In an electrically driven artificial horizon, the axis wander about the pitch axis is controlled by?

A mercury switch at right angles to the pitch axis inducing torque about the roll axis.

355) During a stabilized climbing turn at a constant rate, the instruments which indicate the correct pitch and bank are the?

Attitude indicator, and turn and slip indicator.

356) A RMI (Radio Magnetic Indicator) displays a warning flag which indicates a compass failure. The radio bearing pointers?

Can be used to home to an NDB.

357) An agonic line joins places of?

Zero magnetic variation.

358) Variation is called westerly when?

Magnetic North is to the west of true North.

359) Compass deviation is caused by?

Aircraft magnetism distorting the earth’s magnetic field

360) The direct reading magnetic compass has magnetic correctors for?

Coefficient B and C only.

361) In regard to acceleration errors, they are caused because?

The C of G. lies between the pivot and the equator.

362) The magnetic system of a compass is suspended pendulously to counteract the effect of component?

Z.

363) An aircraft being manufactured in the Northern Hemisphere is parked facing South West?

Parameter P is positive.

364) Parameter P is?

Fore and aft magnetism affecting Co-eff. B.

365) A compass swing should be conducted?

With the engine running.

366) A magnetic material that is easily magnetized is called?

Soft iron magnetic material.

367) Compass accuracy is greatest?

At the Equator.

368) The secular change in variation has a cycle of?

960 years.

369) An aircraft constructed in South Africa has a red pole in the nose and right wing and blue poles in the tail and left wing. The heading during construction is?

315º.

370) The type of compass least likely to suffer from parallax is?

Remote reading compass.

371) When a magnet cannot be made any more magnetic, it is said to be?

Saturated.

372) In direct reading magnetic compass, the effect of dip is counteracted by?

Low centre of gravity.

373) Assuming the compass to be only affected by hard iron magnetism causing deviation, if the latitude changed the deviation would change because?

Of the change in the strength of the Earth’s directive force.

374) With reference to the Sperry Gyrson CL2 compass system. The precession rate of the gyro is kept low in order to?

Suppress turning and acceleration errors.

375) The Sperry CL2 compass system remains synchronized in a turn because?

The signals from the detector unit to the signal selsyn change at the same as the rotor of the signal selsyn turns.

376) The Sperry CL2 compass system does not indicate turning and acceleration errors because of?

The slow precession rate of the gyro.

377) The Sperry CL2 compass system indicates aircraft heading by?

The detector unit senses the angle between the aircraft fore and aft axis and the magnetic meridian.

378) During a turn the remote indicator of a CL2 compass remains synchronized with the actual heading because?

The horizontal gyro due to its rigidity drives the pointers keeping them aligned with the heading.

379) The Central Air Data Computer (CADC)?

Eliminates the time lag error in pressure instruments.

380) Disregarding the effect of compressibility, at a constant IAS the ASI dynamic pressure will be?

The same at all altitudes.

381) If the pitot head and drain hole become blocked by ice during a climb the ASI would?

Over read.

382) Flying at a constant power setting, the highest indicated airspeed will occur when the air is?

Cold and dry.

383) Static pressure is supplied to the ASI in order to?

Balance the static component of pitot pressure.

384) True airspeed is calculated from indicated airspeed by?

Rectifying and correcting for density error.

385) An aeroplane is flying from a warm air mass to a cold air mass at a constant FL and indicated airspeed. The TAS and true altitude?

Both will decrease.

386) The principle and operation of the Mach meter excludes the following errors?

Compressibility, temperature and density errors.

387) An aircraft flying from a cold air mass to a warm air mass at a constant FL and RAS will experience?

No change in Mach number.

388) For an aircraft climbing at a constant Mach No?

The TAS and RAS will decrease.

389) If the static vent becomes blocked during a climb the mach meter will?

Under read.

390) Altimeter instrument errors?

Increase with altitude.

391) Altimeters indicate?

Altitude above the pressure level set on the altimeter.

392) When the barometric pressure sub-scale setting of a servo assisted altimeter is adjusted the altimeter pointer and counters are aligned by?

Mechanically changing the position of the E bar followed by electronic realignment of the E bar.

393) The DGI Directional Gyro Indicator operates on the principle of?

Rigidity in space.

394) The rigidity of a gyro is directly proportional to the?

Speed of rotation and inversely proportional to the moment of inertia.

395) The attitude indicator is primary pitch instrument, other indications of pitch are provided by?

ASI, VSI and Altimeter.

396) The gyroscopic instrument that cannot topple is the?

Turn indicator.

397) Apparent wander of a directional gyro in a stationary aircraft will cause the readings to?

Decrease in the northern hemisphere.

398) Precession or gyro drift of a DGI may be caused by?

Earth rotation, transport wander and reduced moment of inertia.

399) The DGI gyro with the axis aligned north/south may topple due to excessive?

Pitch on north and excessive bank on west.

400) the artificial horizon erection error is due to?

Displacement of the vanes covering the exhaust ports.

401) The artificial horizon outer gimbal has freedom of movement about the?

Roll axis.

402) If an aircraft makes a 360º turn the magnitude of the turning errors of an air driven artificial horizon are at maximum at?

180º into the turn.

403) In an electrically driven artificial horizon gyro wander about the pitch axis is controlled by?

A mercury leveling switch at right angles to the pitch axis producing a torque about the roll axis.

404) The rate gyro at the turn indicator has?

Freedom of movement in one plane only and indicates the angle of bank in a turn using the principle of rigidity.

405) An aircraft enters a balanced rate 1 turn as indicated by the turn indicator. After 2 mins and 15 secs the aircraft has turned through 360º. The rotor speed of the gyro is?

Too high.

406) The magnetism of acceleration errors of a direct reading magnetic compass depend on?

Magnetic latitude and aircraft heading.

407) The requirement of a periodicity in a direct reading magnetic compass is achieved by the use of?

2 or 4 short magnets suspended in a compass liquid.

408) The detector unit of the Sperry CL2 compass transmit s electrical signals to the master indicator signal selsyn?

Which are proportional to the aircraft’s heading?

409) The Sperry CL2 compass system is not affected by the turning and acceleration errors of a direct reading compass due to?

The slow precession rate of the gyro.

410) The Sperry CL2 compass remains synchronized with the aircraft heading in a turn because?

The gyro remains rigid and drives the compass pointers as the aircraft turns about the gyro.

411) An aircraft in the Southern Hemisphere turns left from 175º onto 350º. The aircraft should roll out of the turn on a heading of?

330º.

412) An aircraft heading 180º(C) initiates a left turn onto 350º(C) in the Southern Hemisphere. Initially the compass will indicate a?

Turn in the opposite direction.

413) The Central Air Data Computer (CADC) has a Static Air Temperature (SAT) input in order to?

Calculate TAS from Mach number.

414) It the static vent becomes blocked during climb the ASI would?

Under read.

415) Movement of the ASI needle is proportional to?

Dynamic pressure.

416) If the pitot and drain hole of the ASI become blocked by ice?

The IAS would remain constant in level flight.

417) Converting RAS to TAS using a navigational computer?

The TAS will be lower than RAS if density altitude is lower than pressure altitude.

418) The value of compressibility error of an ASI?

Increases with an increase of airspeed and altitude.

419) ASI errors?

Increase with an increase in airspeed.

420) The Mach meter employs?

An airspeed capsule and an altimeter capsule, their axes 90º apart.

421) When the air temperature is higher than standard at altitude. The indication on an altimeter with QNH set is?


422) The bi-metallic strip in an altimeter corrects for?

Temperature changes in the instrument.

423) A space gyro has?

Freedom of movement in three planes. Mounted in 2 gimbals and the property of rigidity in space.

424) The term “gyro drift” applies to movement of the gyro axis in the?

Horizontal plane.

425) A perfectly balanced space gyro is spinning with its axis vertical at the equator. After 18 hrs the gyro axis will be?

Horizontal with the axis east/west.

426) The directional gyro rider nut corrects for?

Earth rotation wander.

427) The gyroscope properties used by the directional gyro are?

Rigidity to provide a reference datum and precession to maintain the gyro axis in the aircraft’s yawing plane.

428) The transport wander of a DGI in an aircraft flying westbound in the southern hemisphere will cause the DGI readings to?

Decrease.

429) the latitude rider control of the DGI is?

An adjustable weight attached to the inner gimbal.

430) The artificial horizon inner gimbal has freedom of movement about the?

Pitch axis.

431) Bank indication in an artificial horizon is given by?

Movement of the AH casing about the outer gimbal and sky plate.

432) The acceleration error of the electrically driven artificial horizon is less than the air driven type because of?

Less pendulosity.

433) The fast erection system of an electrically driven artificial horizon may be used?

For straight and level flight only.

434) The erection error of the suction type artificial horizon in a turn is?

A lesser amount of bank indicated.

435) A fail flag appears on an electrical turn slip indicator which indicates that?

The turn indicator has failed but the slip indication is valid.

436) The angle of tilt of the rate gyro in a turn indicator is due to?

Primary precession being balanced by secondary precession.

437) In balanced turn the angle of tilt of the rate gyro in the turn indicator?

Increases as the angle of bank increases and the airspeed decreases.

438) The turn indicator uses a rate gyro, and including the spin axis has?

Freedom of movement in 2 planes at 90º to each other and measures the rate of turn in the third plane.

439) An aircraft enters a balanced rate 1 turn as indicated by the turn indicator. After 2 mins the aircraft has turned through 380º. The rotor speed of the gyro is?

Too low.

440) The main reason that the rate gyro of the turn indictor is electrically driven rather than air driven is?

To ensure a constant rotor speed.

441) The purpose of the torque motor in Sperry CL2 compass system is to?

Maintain the gyro spin axis in the aircraft’s yawing plane.

442) The annunciator circuit of the Sperry CL2 compass system?

Monitors the synchronization state of the gyro and assists with manual synchronization.

443) The Sperry CL2 detector unit contains three flux-valves mounted 120 apart instead of a single flux-valve in order to?

Resolve heading ambiguity.

444) The voltage induced into a secondary pick-off coils of a Sperry CL2 flux-valve is proportional to?

The value of component h of the Earth’s magnetic field and direction at which it intersects the flux-valve.

445) An aircraft heading 360º (C) initiates a left turn onto 180º (C) in the Southern Hemisphere. Initially the compass will indicate a?

Greater amount of turn than is actually being made.

446) A magnetic compass will show an apparent turn to the North in the Southern Hemisphere when?

The aircraft decelerates on 270º(C).

447) The magnetic system of a compass is suspended pendulously to counteract the effect of component?

Z.

448) During a turn the remote indicator of a CL2 compass remains synchronised with the actual heading because?

The horizontal gyro due to its rigidity drives the pointers keeping them aligned with the heading.

449) When ambient temperature is warmer than standard at a particular altitude, the altimeter will indicate?


450) The value of the compressibility error of an Airspeed Indicator (ASI) will?

Increase with increase in altitude and true airspeed.

451) the reported QNH of a given station is the?

Station’s barometric pressure corrected at mean sea level pressure.

452) At a constant pressure altitude of 1250ft, a temperature drop from 29 C to 18 C will cause the density altitude to?

Decrease by 1250 ft.

453) Mach No. is equal to?

P – S

S

454) The function of an accelerometer is to?

Measure the force required to accelerate a mass overcoming its inertia.

455) A Lewis Flush Bulb senses?

RAT.

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2 comments:

1.

Chitransh 30 August 2012 at 11:29

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1.

Pratik Poudyal 9 September 2012 at 12:38

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