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Aviation Calculator
Aviation Calculator lnstructions
twA 11 092
or Contents

Contents 2 Altitude - definition and calculation 21

lntroduction 3 General speed calculations 25

lnstructions 4 Speed and flight time
during climb and descent 31
Example of a calculation
Off-course correction 34
Converting units of measurement 8 Point of no return 37
Converting lengths 10
Wind triangle calculation 39
Time, speed, distance 11

Fuel consumption and flight time 15 lmportant abbreviations 50

Convertinq weight and volume 18

02 lntroduction
Absolutely reliable and safe navigation aids are crucial in aviation. ln developing the Aviation Calculator IWA 11092 valuable professio-
Mechanical calculating and navigation devices have substantial naladvice was given to us by numerous aviation institutions.
advantages over their electronic counterparts and have established We are especially grateful to:
their superiority as they do not sufler Irom faults caused by low
power supply or from technical defects. Calculation devices based Jdrg Bohn of lnlercockpit GmbH - Pilot Training Network, Michael
on analogue scales match our way of thinking and imagination and [,4orr of DFS - German Air Traffic Control-, Lufthansa Flight Training
hence aid comprehension of the tasks to be carried out. Each step GmbH Navigation and Meteorological Departments 3
of the task is done manually and is automatically checked by the and the Public Belations Department of the LBA - German Federal
user for feasibility; this reduces the risk of an error. Agency of Aviation.

These are the reasons why pilots need to understand how to use
mechanical devices such as the aviation calculator and why know-
ledge of their use is tested in exams.
03 lnstructions
03.01 General

Ihe Aviation Calculator has scales on one side which enable all The introduction starts off by explaining the general use of the
calculations necessary for p anning a flight to be made. This slde s calculation scales using stralghtforward examples and then leads
matked Flight Calculator. The other side is used for fllght navigation on step by step to the complex arithmetic and geometric f lght
using the wind triang e method. This side is natked Flight Navigator navigation techniques.

The com mon nte rnatlonal abbreviations a nd definitions in Eng ish, N ow look at the Flight Calculator side,of th e aviatlon ca cu lator.
as given ln the Aerospace Dictionary (published by Motorbuch
Verlag 2002) as far as they are avaiable, are used ln the fol owing
examp es o1 calculations.

03.02 What the scale graduations mean

Range Division The scales indicate only the sequence of d gits of a numerical value,
ignoring the declma point. The pos tion of the declmal polnt is then
10 to 15 Who e numbers and tenths determined according to the appl cation.

'15 to 30 Whole numbers and fifths ln most cases the exact value w I not be exact y on a ine, but w ll be
between two graduation marks. ln such case the va ue can be interpola-
30 to 10 Whole numbers and halves ted accordlng to the dlstance from the adjacent graduation marks or
simply read as being the closest lne. As a ru e this is sufficiently
accurate for flght calcu ation purposes.

The values can be read off from the red halr ine on the cursor. n the pic
tures of the calculation examp es the etters marked with an arrow mean
the setting entered > the setting entered, p' the reading and
) p.'ci. ma'l i^gs on lhe n;ght Navlgaor.
 04 Calculation examples

.:* -

t..
-6

04.01 Multiplication

Examp e 4.6 x 1.35

o^
)1 > Set the arrow 10 (inner scale) to 46 (outer scale).
,9oc/
> Read off above 13.5 (inner scale) the result 6.2 (outer scale).

04.02 Division

Examp e 3B:24
The method ls reversed for division:

> Set 24 (inner scaie) to 38 (outer scale).

> Read ofl above arrow 10 the result 1 58

 ob Converting measurement units
The most commonly used units can be converted with the markers on 05.0'l Distances
the calculator. The Iol owing table shows conversion factors for the most
important units. NM Nautical Mile
1 NM = 1.852 km = 1.15 SN/ (Statuate Mile) =6076feet
mile Statuate l\lile
1 mile = 1.609 km = 0.87 NM (Nautical Mile) = 5280 feet
m Metre
1 m = 3.28 feet = 1.09 yd

ft Feet
1 foot = 0.30 m = 0.33 yd

yd Yard
1yd=0.91 m=3jeet

05.02 Speeds 05-03 Volume

lit Knot Litre Lltre

l kt= 0.51 m/s= r.852km/h = 1.15MPH usGAL
1 LITRE = 0.26 US GAL = 0.22 MPGAL
MPH Miles per hour US Galon
MPH = 1.609 km/h = 0.87 k, 1 US GAL = 0.83 IMP GAL = 3 79 LITBE
trup caL
km/h Kilometres per hour lmperia Ga lon
1 km/h = 0.540 kt = 0.62 MPH 1 IMP GAL = 1.20 US GAL = 4.55 LITRE

feet/min Feet per r'inute 05.04 vorume

1 feet/mln = 0.018 km/h=0.005 m/s

m/s second
Metres per kg Kiogramme
1m/s=3.6km/h=1.94kt=197 lkg=221b
lb Pound Pound (lmperial pound)
T lb = 0.45 ks
 oe Converting distances

i'lqf Conversion oi 150 NIM in statute miles and in km

> Set (inner scale) to the marker NAUT M (outer scale)

> To STAT lV 1722 ML and undel km marker

read of[ 278 km.

The fo lowing can be read off in the same way:

metre, yard, feet, lltre, IMP GAL, US GAL.

At the bottom of the outer disk there are

oC
conversion scales Ior and 'F.

oz Time, speed and distance

Calcu ating these parameters is {airly easy keeping in mind that time
is read from the inner scale and distance from the outer scale.

The scale in the green band gives hours. The arrow for t hour reads
as a value of 60 on the inner sca e as t hour = 60 minutes.

Above each value for hours there is an equivalent in minutes,

e.g. above 2 hours is the value 12, i.e. 120 mlnutes.
 "4.,\ 0701 Flight time
4\.\...r
-\*-' i:.:9
ssE') Ground speed GS is B0 kt between two ground marks,
12
which are 70 NM apart.

What f lght time is needed?

> Set the time arrow to B0 (outer scale).

> At 70 NM (outer scale) read o.ft 52.5 minutes (inner scale).

'"% Caution!The distance units must always be compatible for this calculation.
lf the speed is in knats, the distance has to be in NM ot the speed
converted inta km/h. A conversian method will be shown latet.

Fltl' t '''uroi'''l L;:,3,

' "
.' i""l , ,t'i,; iiib'i?tr ;ifeti:/ 13
0702 Distance

Flight time 01 :15 h (75 min), ground speed 120 kt

What dlstance can be covered?

F Set time arrow linner scale) to 120 kt (outer scale).

> At 75 min (inner scale) read off 150 N I\4 (outer scale).
 CautianlThe distance units i11ust always be compatible fat tllts calculatran.
s\*\N$\ lf the speed is in knats, the distance has to be tn NM ar the speed
converted into km/h A canvercion methad will be shawn later.
.YY.'\
.t.\9^q

14
0703 Speed

Distance 28 NIV, flght time 13 mln

What ls the GS?
" ,"*]t"I
ffix" bt
> Set 13 min (inner scale) to 28 NIV (outer sca e).

> Read off 129 kt above the time arrow on the outer scale.

oa Fuel consumption and flight time

-E

08.01 Fuel consumption

15

25 litre/h, flight time 2:40 h

How much fuel is neededi

Set the time arrow to 25 litres/h (outer scale).

Bead off required amount of fuel 66.5 lltre (outer scale) over flight time
2 hours 40 minutes (green time scale).
 You need this calculation af the flight time in arder to determine how long
the aircrcft can stay airbarne with a gtven fuel consumptian and a gtven fuel
load. You need ta take the usable fuel load (reserve minus safety reserve)
;nta cons,detaL;on ;n Lhi. cdlcul"Lian.

08.02 Flight time

16

Fuel consumption 23 litres/h, usab e fuel oad 100 itres.

What flight tlme is possible?

Set the time arrow {inner scale) to 23 litres/h (outer scale).

Read ojf 100 litres (outer scale) possible flight time 4:20 h
(qreen time scale).

fhe average fuel consumption can be estimated after a flight. An additian

!< tt must be allawed ta campensate for taxiing and power checks

17
08.03 Control calculation ofluel consumption

Fllght tlme 4:10 h, Fuel consumption 48 US GAL.

What was the fuel consumption per hour?

> Set 4:10 h (green time scale) at 48 US GAL (outer scale).

> Read off at the time arrow 11.5 US GAL (outer scale).
 os Converting weight to volume
Precise planning of fuelling is a vital part of flight preparatlon. Several
ways of measurlng fuel are used in practice, e.g. by volume (in itres,
lmperial gallons, US gallons) or by weight (in kg or lbs). The converslon
oI one to another is therefore very important.

Conversion using density

Fuei densily is required to convert volume to welght. The mass of a 18
vo ume unit of a material is called density. And the denslty is generaly
given in kg/dm:.

The welght of fuel can be calculated from its volume and vlce versa
by means of its density. The AVIATION CALCULATOR contains
conversion scales Jor'Density" ln kg and in lbs.

F*-**-:"R@]>
one

09.01 Converting volume to weight

'r|oo t 19
x1000 ft
Volume of f ue '120 litres and denslty 0.72 kglltlres
d\ P"!:*8;itw
What is the weight?

) Set volume 120 I (inner scale)to marker tr (outer scale).

> Set cursor hairline to 0.72 Denslty (kg) (outer scale).

Read oif 86.5 kq (inner scale).
 ..s --,

09.02 Converting weighl lo volume

20
Fue load 2500 lbs, density 0.74
How many US GAL is this quantity?

> Set the cursor hairline at 0.74 on the Density (lbs) blue
outer scale and set 25OO {inner scale) under the hairline.

> Read olf the result ol40b US GAL (inner scale) at the US GAL
(outer scale) marker.

ro Calculation and definition of altitudes

10.01 Definitions 10.02 General

HEIGHT Vertical distance above ground Density Altitude and True Altitude are calculated with
Altlmeter scale is set to OFE. the Pressure Altitude as a base.

ALTITUDE Vertical distance to l\y'SL lI the indicated air pressure does not comply with lSA, it needs
(MSL = Mean Sea Level) to be converted to obtain the Pressure A titude. 21
Altimeter scale is set to ONH.
Pressure Altitude is lower for pressures above 1013.2 hPA and
PRESSURE The indicated height if the a timeter scale vice versa (subtract (v add 30 feet per millibar).
ALTITUDE is setto 1013.2 hPa.
(1013.25 hPA = 1013.25 mbar = 29.92 inch HG)

= ISA (lnternationa Standard Atmosphere).

 10.03 True Altitude

lA ( ndicated Atitude) '1T,500 feet

Pressure A titude 12,000 leet
Outslde Alr Temperature OAT 5'C
'^4':Fi 22
Required: True Altitude

ln the ALTITUDE window:

) Using the blue scale, set 12,000 feet to OAT -5'C.

> At lA (lndicated Altitude) of 11,500 feet (inner scale) read oJf

TA (True Altitude) oi 1T,700 feet on outer scale.

10.04.01 DensityAltitude DA

The DensityAltitude (DA) is very important for the performance of an

aircraft. The data in the f ght manua are based on ISA conditions for
the current temperature at the alt tudes indicated. 1f the temperature
deviates from ISA then the DA is different. Thls means that f the
temperature is higher than the DA is a so h gher and vice versa. 23

Correction factors are g ven in most flight manuals, should this not be
the case they can be ca cu ated wlth the Aviat on Calcu ator.
 The temperature is higher than ISA at given altitude The density
-o^
.7, altitude wtll therefare be highet than the barametric altitude-
a>,Az- *- ':^'a
-de
_ ,r-- <
10.04.02 DensityAltitude
':: --)-

: -:@
Dens ty AltiL.de PA 5,000Il
Temperature OAT +20'C
-; .-( _ _+J 24
\_-nJl
-\9, "/ i. oI! Required: Density Altltude

ln the AIB SPEED window:

.o > Set +20"C to 5,000 ft.
Y,/ o'"> n
c:a- o(
/ ln the DENSITY window:
a 's"7 > Read off 6,700 ft at the arrow.

fl General speed calculations

11.01 Detinitions of speed After whlch this gives the

TAS (True Air Speed).
The Air Speed window is for ca culating True Air Speed (TAS).
Four types of flight speeds are used: The scales in the A r Speed window can be used to correct this.

IAS {lndicated Air Speed).

This is the speed read from the instrument, calibrated to I\4SL 25
and SA. This va ue, corrected by the values taken from the flight
manua gives the
CAS {Calibrated Air Speed). ln the fallowing examples it is assumed that the OAT (Outside Ait
For speeds < 200 kt and heights < 10,000 ft, thls value must be Temperature) is known fo( the fllght altitude (e-9. fram the weather report).
corrected by the compressibi ity of alr in the pitot tube to glve the lf theTAS is calculated frcm the outside air temperature measured dunng
EAS (Equivalent Air Speed). the flight allawance should be made far the fact that the indicated
This value corrected by the density g ves the temperature is increased thtough the air friction an the outer surface of
DAS (Density Air Speedl, the aircraft fuselage.
whlch has to be corrected by the temperature deviation of lAS.
 11,02.01 TrueAir Speed

PA 20,000 ft
oAT -40 "C
cAS 350 kt
26

Required: True Air Speed

i$
b
w In the AIR SPEED window:
Set OAT - 40 "C to PA 20,000 ft and
set the cursor hairline on 350 kt (inner scale).

Read of{ TAS 464 kt (outer scale).

11.02.02 Correction by the compressibility

oI air in the pitot tube

27
Keep the unaltered setting of the discs and the cursor
as they are (CAS 350 kt)

ln the Compressibility Factor table read off:

E For PA 20,000 ft the correction {actor .97
F and at.97 the red cursor scale EAS 340 kt (inner scale)
F and above on the outer scale TAS 450 kt.
 11.02.03 Correction ol measurement error
t20 caused by air Iriction
,s..
PA 20,000 ft cAS 350 kt oAT -30'C

*:Ns$*try I> ln the

>
AIR SPEED window: set OAT -30"C tor PA 20,000 ft.
Set cursor hairline on CAS 350 kt (inner scale).
is &rd 't:'b
_7 F qead oflTAS 473 kt (o-ter scdle).
t> Read off at .97 (red cursor scale) 340 kt and 460 kt.

-P. s 2z.
9i E> Read off on the Temperature Rise scale at 2A
460 kt the temperaiure rise of 28 oC (for Ct =1.0)

oAT = - 30'C - 28 "C = - 58 "C.

TAS must be calculated uslng this corrected value.

a\
:$
4

I
*i.'ilSB-
\.r\
'" I
D
In the AIR SPEED window: set OAT -58'C to PA 20,000 ft.
Set cursor hairline on CAS 340 kt (inner scale).
Read ofi TAS 433 kt (outer scale).

11.03 Mach number

29
The l\/lach number M can be calculated on the FLIGHT CALCULATOR
Note an "TEMPERATURE RISE" scale:
slde of the Aviatlon Calculator. This is the TAS of the aircraft re ative to
The upper scale far the temperalure carrectian value af At'C (C, = 1.0) is
the ocal sound velocity. E.g. at a TAS of 200 kt and local sound velocity
based an a temperature recavery coeffictent of Ct = 1.0. This corrcsponds
of LSS 600 kt, the lvlach number wou d be TAS 200/LSS 600 = 0.33 M.
ta the calibratian of madern sensors. The scale below At "C (C, = 0.7)
shaws the equtvalent values for C. = 0.7 This carrespands to the caltbtation
of older types of sensor lf in daubt for older aircftft the C, values can be Local saund velocity depends an temperature- 1n the AIB SPEED windaw
taken from the flight manual. Far examination questions it is rccommended therc is an M mark oppostte the temperature scale- This can be used ta
to give the C.value used for calculating. calculate fhe Mach numb--r
 11.03.01 Local sound velocity M

Given:
TAS 300 kt
oAT - 20'C

Bequlred: M 30

ln the AIR SPEED window:

F Set OAT -20"C to the arrow mark M (kt).

F Bead off opposite TAS 300 (outer scale) M 0.485 (inner scale).

F Opposite N/l 1 (inner scale) read ojf the locaL sound velocity of
LSS 6T I kt (outer scale).

12 Speed and flight times

in climb and descent

,t
og2 Rates af climb/descent are usually given in feet per minute-

12.01 Climb (speed)

A climb ratio of 350 feet per mile s needed to cross a hill.
31
The ground speed GS is 130 kt.

What rate of cllmb (ROC) is needed?

> Set the green tlme arrow to 130 kt on the outer scale.

> Opposite 350jt/miie on the inner scale read ofi

the rate of climb 760 Jeet per minute on the outer scale.
 Rates of climb/descent are usually given in feet per minute

gnLCULATOP
@,,
a',d

12.02 Descent (flight time)

32

How long does it take to descend from 10,000 ft

to 3,000 ft at a rate of descent of 800 ft per minuteT

Set the rate of descent (ROD) 800 feet/min (inner scale) to the altitude
difference 7,000 teet (outer scale).

Read oif at t0 arrow the tlme oI descant of 8.75 min (outer scale).

12.03 Descent (distance from destination)

The distance for commencing the descenl can be calculated

for a known duration of descent.

33
Descent '10 minutes
Ground speed GS 220 kt

At what dislance fronn the destination does the descenl need to start?

> Set time arrow (inner scale) to 220 kt.

> At 10 minutes (inner scale) read off 36.6 NM.

 rs Course corrections

By means of two easy calculations the Aviation Calculator can

correct deviations from course:

Firsi, the error angle ls calculated from the start point and the
given distance.

Then the correction angle is ca culated from the deviatlon and the 34
distance to the destination.

The sum oI the two angles is equal to the ang e by which the course
needs to be corrected.

CALCULATOq
@,t og?

'iez.
,1,
13.01 Example: Course conection
,{
S;:-. A deviation oI 5 NM jrom the start point was recorded after 30
NM. What is the course correction jor the remaininq 40 NM?
35

i*.'ry B--€::=--
-: >
lar:A # -,isB =*
$- -.-E=r
Set the distance at the start point of 30
to a deviation of 5 NM (outer scale).
N l\,4 (inner scale)

9*o.z "'g > Read off the angle o{ deviation of 'lO'at the time arrow.
ilu:tltrilti:ti:liit:
 Set the remaining distance of 40 NM (inner scale)
io deviation 5 Nl\y' (outer scale).

Bead off the complementary angle of 7.5o at the time arrow.

The sum o{ 10' + 7.5'= 17.5' is the angle by which the route has
to be corrected.
36

14 Point of no return (PNR)

With this calculation you can determine the distance you can 14.01 Example: Point of no return (PNR)
cover and slill have sufficient fuel to return to your starting point.
Available Juel 42 IMP GAL
You need to know the fuel consumption, the quantity of fuel at Consumption 5.5 IMP GAL per hour
your disposal and the ground speed lGS). We assume that you have GS outbound 90 kt
already determined GS for the fliqht outbound and inbound. GS inborrnd 150 kt
37
With fuel for approx. 8 hours of fllght and the given GS your PNR
is slightly more than the total flight time.

To determine the exact flight time see the example on page 16.
The result is 7:38 h.

Add the GS outbound and inbound, the sum is 240 kt.

 > Set the flight time 7:38 h to 240 kt on the outer scale.
> Read of{ at GS inbound 150 kt (outer scale)
the time (inner scale) 4:47 h.
ipuas r'

$Jst$ Thus with a total flight time of 7:38 h you can travel outbound 4:47 h at 90 kt.
After this is still suf{icient fuel available for 2:51 h lnbound flight at 150 kt.
1-,"\Y Op to 4:4'l h outbound flight you have enough fuel for the inbound flight.
38

=;t /,
Da not forget to add a safety margin-

:ril )J For converting this value to the related distance you can use the outbound
speed.

> Set the green arrow to outbound speed 90 kt.

) Bead off above PNR 4:47 h {inner scale) the distance
430 N l\,4 louter scale).

rs Wind triangle calculations

The page called FLIGHT NAVIGATOB is to help perform wind triangle

calculations. lt features the three fo lowing components for this purpose:

1. A disk - speed vectors {or the aircraft and the wind can be drawn on the
surface with a solt pencil. The vectors can be set at different angles by
means of the graduations on the graduations on the edge of the disk.
39
2. A slide chart with coordinates for w nd speed, crrcular lines tor TAS of
the aircraft and straight lines for the angle of drift. The LOW SPEED side
is laid out for low speeds, the HIGH SPEED side tor high speeds.

3. A wind cursor with indicator to set the wind direction and scales that
apply to both speed ranges on the chart board.
 15.01 Determining the ground speed GS and the wind correction angle

Given: True course

TC r 10'

w/v 60/40
TAS 170 kt
Requ redrWind correction angle L, GS, true headlng TH
(TC = true course, TH = true head ng)

Set TC 110" to the INDEX arrow

E> Set the m ddle line of the wind cursor to 60".
E> Set the circular TAS arc on the sl de chart belonglng to
TAS 170 kt to w nd speed 40 kt.

l> Read off the w nd correct on angle L at the inlercept = - 10.5'.

e> Read off GS 142 kt at the arc lntercepting the centre of the disk.

TheTH that needs to be manoeuvred is 110'-10.5' = 99.5".

15.02 Determining the wind Irom the drift and the ground speed

Given:
TH 310'
TAS 200 kt
GS lBO Kt
Abdrift d +7'
41

F SetTH 310" at NDEX.

E> Set TAS 200 kt to the middle of the dial.
E> Set the middle ine of the wind cursor to the luff ang e lne +7
and the GS 180 kt circuiar line on the sllde chart.

l> Read off the wind speed 30.5 kt at the intercept.

E> Bead off wind directlon 265" at the end of the cursor.
 15.03 Determining the wind from several drifts

The wlnd can be ca cu ated from the drifts of two true headlngs
if the TAS is known.

G lven:
42
IAS 340 kt
TH 200', q-5'
TH 265", a. + 2'

E Set the circular line GS 340 kt to the mlddle of the disk.

E> set TH 2oo'to tNDEX.

> Mark the drlft ine at 5" in pencil.

F Set TH 265'to INDEX.

> Mark the ntercept + 2'drilt line in penci .

E> Set the w nd cursor to the mark.

F Read off wind speed of 35 kt at the interface.

E> Wind direction 248'can be read off at the end of the wind cursor.

43
15.04 Recoupling Distance 1

TH 320", flight time I minutes, fl ght d stance 31.5 NM

Shift the squared coordinates under
the rotary disk. Set 320'to INDEX.
Set the zero ine of the coordlnate grid (upper edge) to the
Given: nTidd e oI the disk.
TAS 214 kt Draw the first end point at a distance of 31.5 Nlvl verticaly
1',r0"/55 kr downwards.
44
Required: Distance 2
Directlon and distance TH 20', f ght time 5 minutes, fl ght d stance 17 5 NM
from point of coup ing.
Set 20' to N DEX.
Set the zero line of the coordinate grid to the end point of
the first distance.
Draw the second end point at a distance of 17.5 NM
vertica ly downwards.

Distance 3 TH 5B', f lght time 7 minutes, fllght dlstance 24.5 NM

;csr
X
,% Set 58'to INDEX.
Set the zero line of the coordinate grid to the second end point-
;:."'%^ Draw the third end point at a distance of 24.5 NM
";"./.'"' verticaly downwards.

Set Wind 110'to lN D EX.

Wind shift = wind speed x tota f ght t me / 60
=55ktx21 mln/6omin=19NM 45
Set the lower edge of the coordination grid to the third end point.

Draw the wind shift at 19 NIV vertically upwards.

Set the zero lne of the coordinate grid to the middle point.
Turn the end point of the wind shift downwards to the centre axis of the
coordinate grid.
Read off at INDEX the directlon of the coupling destination 355'.
Read off on the coordinate grid the d stance {rom the starting p ace 59.5 NM
 15.05 Course co ection

X The shi{t of the a rcraft from true heading and the d stance from the
start ng point are known. Course error and coLrrse correct on are required.

Given:
TH 14 0'
Tota distance 350 NM, of whlch 190 NM were completed
Shift to the right 24 NM
46
Requlred: Course correction angle

F Set 0' (N) to NDEX.

f> Set the zero lne of the coordinate grid (upper edge)
to the middle of the disk.
> Draw in the shift at a dlstance of 24 NM
vertically downwards.

F Set 90'(E) or 270' (W) to NDEX.

INDEX +
Set 190 NM to the midd e of the disk.
l> Read off route error of 7.2" at lhe marked po nt.

Set remaining distance 160 N N'l ln the middle of the disk.

Head off the correction ang e 8.6'at the marked point.
47

Correct the true headlng 140' by 72'+ 8.6'= 15.8'. NewTH is

124.2".f N can be corrected d rect y with the top scale:
1-+- - - INDEX +
u"*
fiYu,liurHI
\\' 'ito 140
rr i/i r rr Set TH 140" to INDEX.
S\\\\\\\';bO
.\\\\\\\\ \
,
sE
?:
Read off the correctedTH 124.2" a|15.8' of the VAR EAST sca e
 15.06 Wind components for take-off and landing

15.06.01 Head wind

G ven: Wlnd 290" 140 kt

Dlrect on of runway 230'rw

E Set wind direction 290" to lN D EX.

Set the zero po nt for the coordlnate gr d at the middle point
48
of the disk.
Enter wind speed of 40 kt verticaly downwards.

L Set the direction of the runway 230'to NDEX.

D Read off the side wind component of 35 kt vertical to the
horizontal zero line.
The vertica distance of the mark from the zero line is the
head w nd component 20 kt.

15.06.02 Tail wind

- INDEX + G ven: Wind 290" l4A kr
Direct on of runway 60' rw

t> Set wind direction 290'to lNDEX.

r> Set the zero ine of the coordinaie gr d to the m ddle point
of the disk.
Enter wind speed 40 kt verticaily downwards.
49

SFr oIeclro. o''Lnway 60'to L\DTX.

Set the zero point of the coordlnate grid to the wind mark.
F The horizontal distance 31 kt of ihe mark to the centre line ls
the side wlnd component.
The tai wind component can be read off from the centre polnt
of the dlsk and is equal to 26 kt.
16 The most important abbreviations

Term Abbreviation

Altitudes
lndicated Altitude IA
Density Altitude DA
True A titude TA

Speed 50
lndicated Airspeed rAs
Callbrated Airspeed cAs
Equivalent Airspeed EAS
True Alrspeed TAS
Ground Speed GS
Rate o{ Climb ROC
Rate oJ Descent ROD
Mach Number Mach
Local Sonic Speed LSS

Term Abbreviation

Standard Values
Mean Sea Level MSL
lnternational Standard Atmosphere tsA
(1013.25 hPA = 1013.25 mbar = 29.92 inch HG)

Standard
5!
Temperature 15o C
Outside Air Temperature OAT

Course
True Course TC
True Heading TH
True Track TT
True Angle
Wind Correction Angie
twA 11092 / llK T 1

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