Ground Studies for Pilots: Flight Instruments & Automatic Flight Control Systems

8/20/2019 Ground Studies for Pilots: Flight Instruments & Automatic Flight Control Systems

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pitot

connection

electrical

heater

connection


15/232

pitot

head

ASI VSI

ALT

pitot system

static system alternate

static

source

changeover

cock

static

source

static source

drain holes heater element

static pressure

pitot pressure

direction of flight


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diaphragm

type

bellows type

pointer

glass

face

cardscale

pointersetting

knob

aneroidcapsule

fromstatic

source leafspring


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01

2

3

45

6

7

8

9


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01

2

3

45

6

7

8

9

1 2 5 00pointer completes

1 revolution

per 1000 feet


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pointer

pinion

quadrant

capsule

static

pressure

pitot

pressure


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0

50

100

150 200

250AIRSPEED

knots


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altitude capsule

airspeed capsule

ratio arm

ranging arm

static

pressure

pitot

pressure


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0.6

0.5

0.7

0.91.0

1.1

1.2 MACH

1.3

0.8

critical

mach number


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pointer

pinion quadrant

capsule

staticpressure

metering

unit


36/232

FT/ MIN

X1000

0

.5

.5

1

1

2

2

4

4


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vane

pointer

from static source

to reservoir


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inputs computer outputs

static pressure

pitot pressure

total air temperature

transducer

transducer

static

pressure

pressure

pitot

pressuredynamic indicated

airspeed

machnumber

machnumber

trueairspeed

staticair

temperature

trueairspeed

staticairtemperature

altitudememory

altitude

altitudehold

density air

density

systems using adc outputs

flight directorautomatic flight controlaltitude reportinggpwsstall warning

automatic thrust controlcabin pressurisationflight managementflight recorder


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air flowair flow

enginebleed air

out

enginebleed air

in

electricaloutput

connection

sensingelement

heatingelement


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A

s p i n

a x i s

p l a n e o f r o t a t i o n


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X

appliedforce

(a) (b)

appliedforce

appliedforce

appliedforce

precession

(c)

appliedforce

appliedforce

precession

(d)of

applied force

gyro rotor

movement

ofapplied

force

(e)

appliedforce


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Z

Z

X

X

Y

Y

frameinnergimbal

outergimbal

spinaxis

rotor

spindle


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A

A

B

BC

C

D

F

E


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Axis referenced to point in space.

Gyro appears to drift at 15°/hr

Axis referenced to point in space, but aligned with

local meridian. Gyro does not appear to drift


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Axis aligned with point in space and withearth axis. Gyro does not appear to topple

Axis aligned with point in spacedoes not remain perpendicularto earth's surface. Gyro appearsto topple at 15 /hr.

o

cathode

anodeanode

mirror

mirror

mirror

output

laser path


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vacuumpump

directionalgyro

attitudeindicator

inlet filterreliefvalve

exhaust

vacuumgauge


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inner gimbal

outergimbal

rotor

compassscale


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outer

gimbal

air in

air out

air outwedge

rotor


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A B

(a)

C D

(b)

direction of earth rotation

rotor

latitudenut

innergimbal


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aircraftsymbol

horizon bar

actuating pin

counterbalance

innergimbal

outergimbal

bank anglescale

forward

Z

Z

X

X

Y

Y

XX vertical spin axis

YY lateral pitch axis

ZZ longitudinal roll axis


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(a) (b)

(d)(c)

aircraftsymbol

horizon bar

bankanglepointer

bank scale


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(a) (b)

pendulousvanes

innergimbal


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pitchtorquemotor

roll torquemotor

levellingswitches

innergimbal

outer gimbal

input

input

output

principle oflevelling switches


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L

R

forward


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L R L

R

L R L R

L R

(a) (b)

(c) (d)

(e)


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TN

MN

e a r t h ' s

m a g n e

t i c f i

e l d

equat or

magnet ic equat o r

r o t a

t i o n a

l a x i s

TN = true north pole

MN = magnetic north pole

pivot

CG

magnet

magnet

compass card

N


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bowl

compass cardpivot

bellows

support viewingwindow


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N

S

E W

N

S

E

W

N

S

E

W

pivot

CGacceleration

reaction reaction

acceleration

(c)(b)(a)


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N

S

E

W

(a)

N

S

E

W

N

S

E

W

N

S

E

W

aircraft turn

centrifugal

force

aircraft turn

centrifugal

force

(b)

aircraft turn aircraft turn

centrifugal centrifugalforce force

(c) (d)


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TNMN MN

TN

variationwesterly

variationeasterly


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TN CN

MN

variation

easterlydeviationwesterly

1W

180(M)

181(C)


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a.c.

supply

permeable

bars

primary winding

secondary winding


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outputfromsecondarywindings

collector horn


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null-seeking rotor

compasspointer

earth magnetic

field

earth magnetic

field

compasspointer

signal

selsyn

detector unit


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+-

detector unit

signalselsyn

null-seekingrotor

precessioncoil

permanent

magnet

bevel gears

headingindicator

gyro rotor

mechanical transmission


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accelerometer a v s

1st integrator 2nd integrator

a.dt v.dt


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N

N

S

S

pick-offtransformer

pick-offtransformer

force coil

mass

permanent

magnet

permanent magnet

amplifier

primary circuit

secondary circuit

suspension

leaf

spring

a.c. supply

armaturearmature

output


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spinaxis

output

axis

inputaxis

rotor

outer gimbal

inner gimbal

pick-offpick-off

roll motor

pitch motor

azimuth

motor

verticalaxis

r o l l a

x i s

p i t c h a x i s

north

gyro

N–S

accelerometer

E – W

accelerometer

azimuth

gyro east

gyro

stable

platform

frame

attached

to aircraft

aircraft

heading


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azimuth

gyroeast

gyro

n o r t h

g y r o

east –west

accel. n o r t h – s o u t h

a c c e l .

azimuth

motor

pitch

motor

motor

roll

stable

platform

frame frame

N

aircraft

heading


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azimuth

gyroeast

gyro

n o r t h

g

y r o

east –west

accel. n o r t h – s o u t h

a c c e l .

azimuth

motor

p i t c h

m o t o r

m o t o r r

o l l

stable

platform

f r a m

e

f r a m

e

N

a i r c r a

f t

h e a d i n

g


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1st stage integration

accn. N–S d.t= speed N–S

knots

2nd stage integration

speed N–S d.t= distance N–S

nm

start latitude pluschange of latitude

= current latitude

1st stage integration

accn. E – W d.t= speed E – W

knots

2nd stage integration

speed E – W d.t= distance E – W

nm

start longitude pluschange of longitude

= current longitude

N–S

accelerometer accelerometerE – W

gyro – stabilised platform

departure x sec lat

= change of longitude

great circle

great circle

track and groundspeed

track and distance

current position

lat / long


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equator

platform remainsearth horizontal, but

drifts at 15°/hr

platform topples

at 15°/hr

earth rotation

p o l a r a x i s


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OFF

SBY

ALIGN

NAV

ATT

REF

+

+

+

+

READY

NAV

BATT


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TK

CHG

INSERT

1 2 3

4 5 6

7 8 9

0

N

EW

S

HOLD CLEAR

ALERT BATT WARN

W

P

T

MAN

AUTO RMT

TK/GS

HDG/DA

XTK/TKE

POS WPT

DIS/TIME

WIND

DSR TK/STS

TEST

DIM

4


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107/232

left

left

left

right

right

right

light sensor light sensor

control panel control panel

EADI EADI

EHSI EHSI

symbol symbolsymbolgenerator generator generator

centre

data busses

VORDMEILSRAD ALTWXR RADARIRSFCCFMCS

VORDMEILSRAD ALTWXR RADARIRSFCCFMCS

(left) (right)(ctr)IRSFCC

(ctr)IRSFCC

TMC TMCTMC(l&r)VORDMEWXRIRSFCC

(ctr)IRSFCCFMCSILSRAD ALT(right)FMCS


108/232

ADI

DH REF

BRT

RST

ON ON ON ON ON

ON

WXRBRT

RANGE

HSI

10

20

40

80 160320

NAV

PLAN

VOR

ILS

NAV

VOR

ILS

MAP

CTR

MAP

EXP

FULL

decision height

reference indicator

decision height

setting knob

decision height

reset button

EADI brightness

control knob

EHSI range

setting knob

EHSI map mode

selector buttons

(select features to be added to MAP display)

EHSI manual

brightness co

weather radar

display butto

VOR/ADF NAVAID ARPT RTE

DATA

WPT

MAP


109/232


110/232

10 10

10 10

20 20

20 20

GS 350 DH 100

1850

CMD

LOC

LNAV

F

S

A/T

GS

SPD

VNAV PTH

700

roll pointer (W) roll scale (W)

ground

speed (W)

speedscale (W)

speedpointer (M)

autothrottlemode (G)

armed pitchmode (W)

engagedpitch mode (G)

autothrottlestatus (G)

slip indicatorlocaliserdeviation

pointer (M)

localiserdeviation

scale (W)

selected

decisionheight (G)

radioaltitude (W)

display below 1000ft

flight director

command bars (M)

aircraft symbol (W)

glideslope deviation

pointer (M)

glideslopescale (W)

AFDS status (G)

armed roll

mode (W)

engaged roll mode

W whiteG green

M magenta


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1 8

21

2 4

209

40

KHND

SED

CENTR

PERRY

112.2

40

28.5 NM 0923.5ZTRK M

distance tonext waypoint (W) magnetic track (W) heading pointer (W)

headingset bug (M)

ETA next

waypoint (W)

expanded compassrose (W)

verticaldeviationpointer (M)

verticaldeviationscale (W)

trendvector (W)

aircraftsymbol (W)

selected ILSfrequency (G)

lateral deviationpointer (M)

lateral deviationscale (W)

airport (C) radio navaid (C)

off-route waypoint (C) waypoint (active M, inactive W)

wind speedand direction (W)

range toselectedaltitude (G)

weatherradardisplay(G, Y, R, M)

instantaneoustrack (W)

rangescale (W)

C cyanW whiteG greenY yellowR redM magenta


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1 8

21

2 4

20985 NM 0923.5ZTRK M

N

BKE

SOC

GNGN

0

1 8 9

2 7

3 3 3 0

2 4

2 1

1 5 1 2

6

3

MHDG 308

ILS75

112.2

DME 34.0


113/232

MHDG

15 1 2

139DME 27.5

10

25

ILS 112.2


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engine sensors system sensors other systems

N1

N2

N3

EPR

EGT

FF

oil temp

oil press

oil qty

vibration

hyd presshyd qtyhyd syst tempfg cont surfaces

elect sys (I, V, F)

csdu tempECS tempsAPU (EGT, RPM)

brake temps

FCC

TMC

EEC

FMC

rad altADC

display select panel rightcomputer

leftcomputer

upper

display unit

lower

display unit

displayswitching

caution andwarning lights

standbyengineindicator

maintenance panel


117/232

EPR

N 1

EGT

1.52 1.52

98.2 98.0

695 692

V

1.52

V VVV V V


118/232

EPR

N 1

EGT

1.52 1.52

98.2 98.0

695 692

VV VVV V V

R ENG OIL PRESS

R ENG OIL TEMP

R ENG OIL QTY

OIL PRESS

OIL TEMP

OIL QTY

primary panel

secondary panel

warning message (R)

cautionary message (Y)

advisory message (Y)(indented)

52 33

100 115

20

12

VV VVV V V

secondary panel

HYD QTYHYD PRESSOXY PRESS

APU

L C R

1.00 0.97 0.99

3000 3015 2995

1785

EGT 498 RPM 98

AIL AILELEV

RUD

CABIN ALT AUTO 1ELEV FEELA/SKID OFFPARKING BRK

system states

flyingcontrolpositions

despatchstates


119/232

ENGINE STATUS

DISPLAY

EVENTRECORD

L RAUTO

COMPUTER BRTTHRUSTREF SET

L RBOTH MAX

INDRESET

BRT

BAL


120/232

EPR

N 1

EGT

1.52 1.52

98.2 98.0

695 692

OIL PRESS

OIL TEMP

OIL QTY

VIB

N2

48 50

102 108

20 21

1.7 1.7

98 99

7.8 7.8FF

N 2FAN

TAT -20C

AUTO

ON

EPR

N

EGT

N

1

2

115115

865 865

110 110

1.65 1.651.52 1.52

98.2 98.0

692695

94.0 93.9

maximumlimits

self-testswitch


121/232

left hand display right hand display

symbol symbolgenerator generator

warning lightdisplay unit

ECAMcontrol panel

system dataanalogueconverter

flight warning flight warningcomputer computer

analogue inputs

aircraft systemsaircraft systemsdata inputs data inputs


122/232

FAULT

OFF

FAULT

OFFOFFOFF BRT BRT

LEFT DISPLAY RIGHT DISPLAY

CLR

STS

RCL

ENG HYD AC DC

BLEED COND PRESS FUEL

APU F/CTL DOOR WHEEL

SGU 1 SGU 2

synoptic display switches

SGU select switches


123/232

GEN 2

FREQ......................DISCONNECT CSD 2 DRIVE

ELEC AC

BUS 1 BUS 2

GEN 1 GEN 2

115 400 115 420V HZ HZV

CSD 2 DRIVE DISCONNECTGEN 2 OFF

ELEC AC

BUS 1 BUS 2

GEN 1 GEN 2115 400V HZ

ELEC


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8/20/2019 Ground Studies for Pilots

Documents

Ground Studies for Pilots: Flight Instruments & Automatic Flight Control Systems