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Mod 13 > 13.8 Instruments > Flashcards

13.8 Instruments Flashcards

1
Q

Instrument classification

A

Flight instruments

Engine instruments

Navigation instruments

Other systems

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2
Q

Flight instruments

A

Attitude
Altitude
Air speed
Direction
Ratés

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3
Q

Basic T

A

TL - air speed
TC - attitude indicator
TR - altitude
BC - heading indicator

BL - turn coordinator
BR - VSI

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4
Q

Engine instruments

A

Power plant status
Amount of power produced
Instrument Ts and Ps
Electrical system health

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5
Q

Nav instruments

A

Nav info eg VOR ADF DME
GPWS
Weather avoidance

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6
Q

Other systems

A

Status of systems anti ice etc
Pressurisation systems
Heating and air conditioning

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7
Q

Instrument panels are

A

Attached so to provide the crew with correct viewing angles

Some are shock mounted to prevent engine and air frame vibrations so they don’t obscure reading and reduce service life

Also painted to reduce glare usually Matte colours

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8
Q

Atmosphere composition

A

Nitrogen 78%
Oxygen 21%
Other gases 1%

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9
Q

Troposphere

A

Contains the weather system

Temp drops approx 2c per 1000ft

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10
Q

Tropopause

A

Between 8-18km pôle to equator
25,000-57,000ft

Temp stops dropping with increasing altitude

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11
Q

Stratosphere

A

Temperature is considered constant for civil aviation use

Between 8-18km to 50 km

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12
Q

Temperature units

A

Celsius 1-100c melting point of ice and boiling point of water

Kelvin (absolute 0) -273c - all molecules movement stops

Fahrenheit - 0f - 212f 32f = 0c 212 = 100c

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13
Q

Temp conversions

A

F= 32 + (9/5 C)

C= 5/9 (F-32)

K= C+273.15

R= F+459

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14
Q

Tropopause temp values

A

Equator - -80c
45 degree latitude - -56c
Poles -45c

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15
Q

Temp and aircraft performance

A

At a given pressure an increase in temperature results in a decrease in density

Therefore less lift for increased temps

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16
Q

Pressure

A

Pressure = force / area = mass x acceleration / area

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17
Q

I’m reassure

A

In the atmosphere the pressure is caused by the mass air acting under the force of gravity on a given area

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18
Q

Pressure

A

Force always acts at right angles to the surface that the pressure is exposed to.

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19
Q

Pressure

A

If the volume is reduced the molecules act on a smaller area thus the force exerted per area unit increases and vice versa

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20
Q

Pressure units

A

PSI
N/m2
Pascal
Millibar
hpa

1 pascal = 1 N/m2

1mb = 1hpa

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21
Q

Mean sea level pressure

A

29.92 in hg
1013hpa

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22
Q

Pressure altitude high to low look out below

A

High pressure to a low pressure without pressure compensation will mean the aircraft’s lower than indicated

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23
Q

Isobars

A

Are lines on a weather map joining together places of equal atmospheric pressures

Measure the atmospheric pressure in millibars

Eg 1004 indicates a high pressure

976 indicates a low pressure

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24
Q

Density altitude

A

Is the altitude relative to the standard atmosphere conditions at which the air density would be equal to the indicated air density at the place of observation

Ie density altitude is air density given as a height above mean sea level. Density altitude can also be considered to be the pressure altitude adjusted for non standard temperature

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25
Q

Absolute pressure
Gauge pressure
Differential pressure

A

Absolute pressure is the measure of the barometric pressure + gauge pressure

Gauge pressure reads the relative pressure above the ambient atmospheric pressure

Pabs = Pg + Pabs

Diff pressure is the difference between internal cabin pressure and external pressure for aircraft

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26
Q

Static pressure

Ps

A

Is the pressure of a gas when the gas is stationary

(Altitude)

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27
Q

Dynamic pressure
Ram pressure
PD

A

Is the component of fluid pressure that represents fluid kinetic energy

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28
Q

Pitot pressure
Total pressure
PT

A

Combines dynamic pressure and static pressure

(Air speed)

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29
Q

Density

A

Reduces with altitude

Density = mass/volume

Grams or kg per cubic metre
Pounds per cubic feet

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30
Q

The speed of sound

A

Is dependant on air temperature

Higher the air temp the higher the speed of sound

Standard sea level speed of sound
340m/s
661K

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31
Q

Mach number

A

Is the ratio of the speed of aircraft to the local sound speed and expressed as a Mach number

Mach number = aircraft speed/sound speed

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32
Q

Mach number

A

For a given airspeed will depend on altitude.

As altitude increases the Mach number also increases because of the lowering of the local sound speed

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33
Q

Critical Mach number

A

Used in aerodynamics

Is the lowest mach number at which the airflow over some point of the aircraft reaches the speed of sound but does not exceed its

Mcrit is a fixed value for any given aircraft design and configuration and is always less than 1.

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34
Q

Standard atmosphere SI values

A

Pressure at MSA - 1013.25HPA

Temperature at MSA - 15c (288K)

Density at MSA - 1.225kg/m3

Temp lapse rate (tropopause) 1.98c per 1000ft

Temperature lower stratosphere -56.5c (216.7k)

Sound speed at MSA - 340m/s (661k)

Gravity 9.81m/s

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35
Q

Variable resistance systems

A

Parameter controls the resistance when it changes so does the resistance output

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36
Q

Synchros

A

120 degree separation between phases

Voltage in the stator coils depends on the angles between the rotor coil and each stator coil.

When we turn the rotor the magnetic field in the stator also turns and the voltages in the stator coils change

Voltage reference relates to angular position

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37
Q

LVDTs

A

Change linear position information into electrical signals

Flight control surface position

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38
Q

Resolvers

A

Two stators @ 90 degree to each other

Produce a sine and cosine as the rotor is turned

Can give a angular position

Eg throttle lever position

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39
Q

E and I bar

A

Magnetic unit that is used as a error detector in systems in which the load is not required to move through large angles

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40
Q

RVDTs

A

Change angular position into electrical signals

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41
Q

Servo loop with DC motor

A

Anytime there is a difference between the two signals the motor drives the load and feedback until both signals are equal

Polarity of difference signal decides the direction of rotation

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42
Q

Servo loop with AC motor

A

More torque use AC motor

A chopper circuit makes AC from a DC signal, to drive the AC motor with this signal we need an extra amplifier. System then runs like a DC system

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43
Q

Two phase servo motor

A

The AC two phase induction motor servo motor may be very small but powerful

Stator has two fields they are represented symbolically by two coils drawn at right angles to each other

Counter clockwise rotation - variable field angle 0 degree 400hz and other field at 90 degrees

Clockwise rotation - variable signal reversed

Braked - disconnect either the variable or fixed field

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44
Q

Absolute pressure instruments

A

Aneroid capsule

Air pressure increases capsule thickness decreases

Air pressure decreases the capsule expands

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45
Q

Gauge pressure

A

Is measured from a existing barometric pressure and is the pressure that has been added to a fluid over and above atmospheric pressure

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46
Q

Bourdon tube

Gauge pressure r

A

Flattens curved Bronze tube sealed at one end and connected to a gear at the other, as the pressure increases the tube straightens which turns the gear and pointer

Used for high pressure systems like oil pressure

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47
Q

Bellows

A

Lower pressures such as instrument air pressure are measured with a bellows mechanism.

Similar to a aneroid capsule but opposite

Air pressure increase the bellows expands

Air pressure decreases bellows contracts

Sector gear drives a pointer

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48
Q

Differential pressure

A

Uses a differential bellows

Takes two pressures and indicates the difference

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49
Q

Strain gauges

A

Resistance changes as force is applied

Piezo resistive

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50
Q

Variable frequency signals

A

As a parameter increases or des read so does the frequency output

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51
Q

Temp measuring

A

Bimetallic strip - 2 strips welded together then as heated one expands and moves the pointer

Gas expansion of a bourden tubes

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52
Q

Temp dependent resistors

A

NTC - resistance decreases with increase in temp

PTC - resistance increases with increase in temp

Temp sensing bulb - resistance increases with increase in temp

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53
Q

Thermocouples

A

Chromel alumel

Compares reference junction to hot junction

Uses voltage produced from the thermocouple to determine the temp diff between the hot and cold junction

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54
Q

Quantity measurement DC system

A

Reed switches
Magnetic floats

Variable resistor
Tank unit
Current measure

Ratio meter to minimise error

55
Q

Quantity measurement capacitance type

A

Uses a probe which uses the fluid level for the dielectric

More fluid equals higher capacitance

56
Q

Ultrasonic fuel measurement

A

Uses ultrasonic pulses to send receive signals using time taken to reflect for measurement,

also needs to know density

Water can effect the system

Works similar to capacitance

57
Q

Stall warning lift detector

A

Leading edge of wing detector penetrates are flow, when lift stagnates and stalls it allows the switch to make causing the stall warning alert

58
Q

Stall warning stick shakers

A

Alerts the crew to a imminent stall by setting the shakers off and also the alerting annunciation and aurals

Some aircraft also have stick pushers

59
Q

AOA vane

Alpha vane

A

Sends Aircraft attitude and AOA data to the stall warning computer

Vane moves a internal synchro for the position signal

Can indicate on the EFIS

Heated

Lightning strike inspection to make sure they are still free moving and not arc welded together

60
Q

VFR instruments

A

Air speed
Altitude
Compass

61
Q

IFR instruments

A

Airspeed
Altitude (adjustable)
Compass
Attitude indicator
Directional gyro
Rate of turn
Clock
VSI

62
Q

Pitot static systems

A

Pressure decreases with altitude
Nonlinear

1Hpa per 28ft

63
Q

Small aircraft pitot statics

A

Pitot goes straight to the airspeed indicator

Two flush static ports and sometimes takes internal cockpit pressure on a unpressurised fuselage

64
Q

Large aircraft pitot statics

A

More complex system
Uses CAPT, FO and Aux ports
Air data modules used

65
Q

Pitot tubes

A

Ram air pressure

Electrically heated

66
Q

Static port

A

Uses static air for sensing

Positioned so that the airflow is not disturbed around the port

Position error is compensated by fitting ports to both sides of the aircraft to statically balance

In event of yaw side slip etc

67
Q

Static air temperature

A

Temperature of the Undisturbed air around the aircraft.

TAT temp + M number to calculate

Used to calculate true airspeed

68
Q

TAT

A

Used for engine power settings

Compressed air temperature

Difference between SAT and TAT is the ram rise

Ram rise is negligible below M.2

Over Mach .2 air speed increase the temp is higher than still air temperature due to kinetic heating and adiabatic heating

69
Q

Altimeters

A

Uses the principle of a barometer with gears and pointers attached

Indicates in feet

Aneroid barometer reads altitudes using static air pressure

Some have adjustable Barosettings to adjust for local pressure altitudes

QNH local air pressure at mean sea level

QFE height aviver ground at the airfield

70
Q

Drum type altimeters

A

Uses a stack of bellows to drive the pointers

71
Q

Sensitive altimeters

A

Uses a minimum of two aneroid capsules to increase accuracy

72
Q

QFE / standard

A

Takes mean sea level pressure 29.92” or 1013 mb usually set at 10,000ft for aircraft separation

73
Q

QFE

A

Indicates 0 on the altimeter whilst on the ground at the airfield

74
Q

QNH

A

corrected pressure for sea level

75
Q

Altimeters

A

Large needle 1000ft
Small fat needle 10,000ft

Fitted with a vibrator to reduce lag and sticking

76
Q

Altitude reporting and altitude encoding

A

Sends altitude data to the transponder for reporting

77
Q

Altitude alerting

A

Approaching selected altitude 900ft to go alt light on the altimeters comes on

Deviating 200ft from selected altitude sets off the alert

78
Q

RVSM

A

FL 290-410

Allows 1000ft separation

+/- 25ft at 5000ft

+/- 125ft at 50,000ft

Minimum equipment

Two primary altitude measurement systems

One auto altitude control system

One altitude alerting device

Transponder system

79
Q

Scale error

A

Baro set standard and must be within limits

80
Q

Hysteresis

A

Is essentially a lagging of the indication caused by the deflection of the metal in the diaphragm not keeping up with the pressure changes

81
Q

After effect

A

Error shows up by the altimeter not returning to its original reading after the hysteresis test

82
Q

Friction

A

Non servo altimeters test how much friction is needed to keep the instrument reading accurately

83
Q

Case leak

A

Performed at 18,000ft pressure to be sure it does not leak more than 100ft in one minute

84
Q

Barametric scale error

A

Test determines that the movement of the barometric scale has the proper effect on the pointers

85
Q

VSI

A

It is vented to the inside of the case through a diffuser which is a calibrated leak. (Altimeter sealed or evacuated)

Aircraft climbs pressure inside the capsule begins to decrease to a value below the inside of the case and the capsule compresses causing the gears and pointers to indicate

86
Q

Air speed indicator

A

Principle of operation formula

PT= 1/2pV2 + PS

87
Q

ASI

A

Is a differential pressure gauge that measures the difference between the pitot and static pressure.

In a airtight case in which a thin metal capsule is mounted PT taken into the capsule and internal case uses PS

The capsule expands in proportion to the difference between PT & PS which then drives gears and pointers

88
Q

Square law compensating

A

Diff pressure varies with the square of speed

Uses a tuning spring to compensation

89
Q

1 Knot =

A

1.15 miles

1.8km

90
Q

Indicated Airspeed

A

Is the indicated pitot static airspeed without any compensation or error correction

91
Q

Calibrated airspeed

A

Is indicated airspeed corrected for instrument errors position error and installation error

92
Q

Equivalent air speed

A

The speed at sea level

93
Q

TAS

A

True airspeed differs from equivalent air speed because it hr air speed indicators are calibrated at seal level ISA conditions

Corrected for density

94
Q

Ground speed GS

A

Ground speed is the true airspeed corrected with wind speed and represents the speed of an aircraft relative to the ground

95
Q

Mach number

A

TAS / local speed of sound

Which changes with altitude

96
Q

Over speed warning

A

Uses Vmo and MMO for over speed warning

97
Q

Air data computer

A

Used in place of direct reading indicators (EFIS)

Pitot static computers
Gyroscopes
Accelerometers
TAT

Air data modules take in analogue raw data then convert it to arinc and send it to relèvent sources

98
Q

Gyro scoping instruments

A

Spins and has two characteristics

Rigidity (position)
Directional/horizon/ position gyros
Provides stable reference for direction and attitude measurement

Precision (rate)
Turn and slip / turn coordinators
Force applied is effected at 90 degrees to the force

The amount of precision is equal to the amount of force applied

99
Q

Types of Gyros

A

Vertical gyro 2degrees of freedom
Angular displacement from vertical direction
Artificial horizon / attitude reference / weather radar

Directional gyro 2D of freedom
Sensing angular displacement of horizontal direction azimuth heading
Compass / heading

Rate gyro 1d of freedom
Senses Aircraft angular rate of all 3 axis
Turn & slip / turn coordination

Rate integrating gyro 1d of freedom
Platform stabilisation for INS
Sensing the Integral of aircraft angular rate

100
Q

Erection of vertical gyros

A

Air
Electric motors
Spinning balls

101
Q

Directional gyro slaving

A

Directional gyro must be set to agree with the magnetic compass and it too must be checked periodically

At least every 15 mins to make sure it hasn’t drifted our agreement with the compass

102
Q

HSI

A

Heading indicator combined with VOR/ILS DISPLAY

Usually under the artificial horizon

VOR indicator left/right to from indicators

103
Q

Gyro wander

A

Any deviation of the gyro spin axis from its set direction is known as gyro wander (drift)

104
Q

Real wander

A

Any physical deviation of the gyro spin axis

Assy metrical bearing friction, unpredictable or able to compensate for

105
Q

Apparent wander

A

Gyro spin axis does not physically wander away from its preset direction but to an observer it will appear to change direction

Because the gyro maintains its direction with respect to a fixed point in space

360 d a day

15 degrees an hour

106
Q

Gyro drift

A

Directional gyro drift
Earth rate apparent drift 15d an hour x sin latitude

Vertical gyro drift
Earth rate apparent drift 15d an hour x cos latitude

107
Q

Altitude gyro

A

Mounted in a double gimbal and has freedom about 2 axis

108
Q

Rate gyro

A

Single gimbal freedom about one axis

109
Q

Attitude and heading reference system

A

Replaces mechanical gyros
With sensors on the 3 axis and linked to the EFIS

Must be connected to a magnetometer

Can be combined with air data
ADAHRS

110
Q

Turn and slip indicators

A

2 minute 3 degree second

4 minute 1.5 degree second

2 min turn standard for light aircraft

4 min turn standard for heavy aircraft

111
Q

Turn coordinated

A

Similar to a turn and slip but gimbal axis is tilted 30 degree so it will read when the aircraft rolls and yaws

112
Q

Gyro instrument pneumatic types

A

Some aircraft you pneumatic gyro systems

Electrical or Venturi systems

113
Q

Wet type vacuum pumps

A

Uses oil in the air system via a metered pump and is discharged with the air

Low altitude

Steel vanes in a steel housing

114
Q

Dry air pump

A

Carbon vanes remove the friction of steel on steel

High altitude

115
Q

Gyro electric motor system

A

Speed is between 6000 and 20,000 rpm

116
Q

Advantages of air driven gyros

A

Cheap
Easy to maintain
Operate without power
Higher rigidity is possible
Operating RPM is more consistant
Performance is not affected by altitude
I formation transmitted to other systems
More freedom about the axis
Instrument case completely sealed

117
Q

Air gyro disadvantages

A

Requires being at operating speed for full rigidity

Rotor speed depends on mass flow

Ingested dirt or moisture will create corrosion and bearing wear

Requires a air tight system to operate

118
Q

Direct reading compasses

A

To compensate for inclination (tilting) the compass float is weighted on the side nearest the equator

Variation is the difference from a geographical pole to the magnetic poles they are compensated for on aeronautical maps

Deviation caused by the magnetic influences of the compass mounted on the aircraft. A compass swing is performed to minimise deviation and residual deviation is compensated for by use of a deviation card

Soft (earths mag field acting on a material) and hard (permanent) magnetism

Total deviation = A + B sin heading + C cos heading

119
Q

EASA compass regulations

A

Deviation card must be near the instrument and show deviation of mag heading no more than 45 d increments

Compass after compensation must not greater than 10 degree deviation

Distance between the compass and any interference shall be so that it doesn’t cause more than 1degres of deviation

Any flight control or undercarriage movement will not cause more than 1degree movement

The effect of the aircraft permanent and induced magnetism as given by coefficients B & C together with any associated soft iron components shall not exceed

A) after correction the greatest deviation on any heading shall be 3D for direct reading compasses and 1D for remote indicating compasses

B) emergency standby compasses and non mandatory compasses need not fully comply with EASA regs but evidence of satisfactory installation is required

120
Q

Compass swing should be carried out

A

On aircraft acceptance
New compass fitted
Periodically every 3 months
Major inspection
Following a change in magnetic material of the jet
If aircraft is moved to a new airfield
Following a lightning strike or heavy static
If stood on the same heading for more than 4 weeks
When carrying ferrous freight
Iaw MPD
When compass deviation is suspected

121
Q

Compensation

A

Mechanical
Electrical

122
Q

Remote reading compass

A

Uses a flux valve in the wing tip or tail which uses earths flux lines to give readings

With a directional gyro

Manual synchronising knob

123
Q

FDR

A

Required with MTOW greater than 5700kg and 9 pax

Must retain at least the last 25 hours

10 hours is MTOW is less than 5700kg

Records:

Altitude
Airspeed
Heading
Attitude pitch and roll
Acceleration
Thrust/power settings
Config of lift drag devices
Radio transmission keying
Use of AFCS
AOA
Air temperature

Aircraft MTOW greater than 27,000kg also has to record

Primary flight control positions
Pitch trim
Primary nav info as per EFaiS to crew
Flight deck warnings
Landing gear position
Radio altitude

Must be recording when the aircraft is capable of moving under its own power

Engine start to 5 mins after shutdown

27000kg 32 channels
Less than 5700kg 15 channels

Preflight test switch
Bite
Under water locator beacon 37Khz lasts 30 days

Parameter input formats
Analogue
Digital
Discrete

Positioned in a place that will minimise as much as possible
Damage
Fire
Heat
Shock

Powered by hot battery bus usually

124
Q

EFIS

A

PFD
MFD
EIS

On light aircraft sometimes the EIS is combined into the MFD

125
Q

G1000

A

Two options
Autopilot built in
Autopilot separate

Two SD slots
Top NDB & software loading
Bottom terrain databases

MEMS technology solid state sensors to provide attitude and heading references

Magnetometer digital compass

Transponder minimum mode C

126
Q

EICAS
ECAM

A

Engine indicating crew alerting system
Will give cautions warnings memos status

Electronic centralised aircraft monitoring will give a fault and resolution and serves primary systems

127
Q

ECAM

A

Level 1-3 failure

Level 1 - failure to system that degrades it (amber light)

Level 2 - system failure but no direct consequence to flight safety (amber light single chime)

Level 3 - over speed, fire, stall (red warning repetitive chime)

Data displayed in schematic checklist format

128
Q

Terrain awareness and warning system

A

Class B - 4 functions

Foward looking terrain avoidance looks forward and down
Premature decent alert
Attention alerts

Class A - 5 functions
Terrain awareness display

129
Q

GPWS

A

Mode 1 - excessive decent rate 2450 ra and below

Mode 2 - terrain rising rapidly

Mode 3 - sink rate TOGA

Mode 4 - landing configuration for landing terrain closure

Mode 5 - ILS glideslope

Mode 6 - alerts minimums, DH, bank angle

Mode 7 - (optional) wind shear

130
Q

EGPWS terrain picture

A

Solid red - warning terrain approx 30s to collision

Solid yellow - caution terrain approx 60s to impact

50% red dots - more than 2000ft above ref altitude

50% yellow dots - 1-2000ft above ref altitude

25% yellow dots - 500-1000feet above ref altitude

25% green dots - 500-1000ft below ref altitude

12.5% green dots - 1000-2000 feet below ref altitude

Black - no close terrain

Magenta - unknown terrain

131
Q

Terrain clearance floor

A

Modifies terrain database for recognised airfields to cancel nuisance warnings

132
Q

Traffic awareness

A

Traffic information service - using ADS-B to transmit the traffic position information from a ground facility to the aircraft which displays it on the PFD and MFD

Traffic advisory system - this is an indépendant airborne system utilising directional antennas and a suitable mode S transponder

133
Q

TCAS

A

Fitted to all aircraft MTOW greater than 5700kg and carrying more than 19 pax

Directional antennas
Transponder mode s

134
Q

Standby instruments

A

ASI
Attitude indicator
Altimeter
Heading indicator

Mod 13 (22 decks)

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