AIRSPEED CALIBRATION - Axenty Aviation 152 PD.pdf · 40 -20 a 20 40 60 DEGREES - CELSIUS Figure 5-2. Temperature Conversion Chart 5-9. SECTION 5 PERFORMANCE CESSNA MODEL 152 STALL

SECTION 5PERFORMANCE

CESSNAMODEL 152

AIRSPEED CALIBRATION

CONDITION:Power required for level flight or maximum rated RPM dive.

Figure 5-1. Airspeed Calibration

5-8

FLAPS UP

KIAS . 40 50 60 70 80 90 100 110 120 130 140KCAS 46 -53) 60 69 78 88 97 107 117 127 136

FLAPS 100

KIAS 40 50 60 70 80 85 - -. . - - . - - . - - -

KCAS 44 52 61 70 80 84 - - - - - - - - - - - -

FLAPS 300

KIAS 40 50 60 70 80 85 - -. - - - - - --

KCAS 43 51 61 71 82 87 - - - - - - - - - - - -. - - -

CESSNAMODEL 152


TEMPERATURE CONVERSION CHART

120

100

80

60f--wIZw0:I

« 40u..

(J)wW0:<:Jw

0 20

a

t20

40

40 a 40-20 20 60

DEGREES - CELSIUS

Figure 5-2. Temperature Conversion Chart

5-9


CESSNAMODEL 152

STALL SPEEDS

CONDITIONS:Power Off

NOTE:

KIAS values are approximate and are based on airspeed calibration data with power off.

MOST REARWARD CENTER OF GRAVITY

MOST FORWARD CENTER OF GRAVITY

Figure 5-3. Stall Speeds

5-10

ANGLE OF BANK

WEIGHT FLAP0° 30° 450 60°LBS DEFLECTION

KIAS KCAS. KIAS KCAS KIAS KCAS KIAS KCAS

UP 36 46 39 49 43 55 51 65

1670 10° 36 43 39 46 43 51 51 61

300 31 41 33 44 37 49 44 58

ANGLE OF BANK

WEIGHT FLAP0° 30° 45° 60°LBS DEFLECTION

KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS

UP 40 4B 43 52 48 57 57 6B

1670 100 40 46 43 49 48 55 57 65

300 35 43 38 46 42 51 49 61

CONDITION:Flaps 10°Full Throttle Prior to Brake ReleasePaved, Level, Dry RunwayZero Wind

TAKEOFF DISTANCE

I SHORT FIELD I

NOTES:1. Short field technique as specified in Section 4.2. Prior to takeoff from fields above 3000 feet elevation, the mixture should be leaned to give maximum RPM in a full throttle,

static runup.3. Decrease distances 10% for each 9 knots headwind. For operation with tailwinds up to 10 knots, increase distances by 10%

for each 2 knots.

4. For operation on a dry, grass runway, increase distances by 15% of the "ground roll" figure.

Cf.......... Figure 5-4. Takeoff Distance

~oat?:!tJoot?:!oot"Z>CI1/.I:)

'"dt?:!~":1000~t?:!~o>:jZOoZt?:!CI1

TAKEOFF OOC 10°C 20°C 30°C 40°C

WEIGHTSPEED PRESS

LBSKIAS ALT TOTAL TOTAL TOTAL TOTAL TOTAL

LIFT AT FT GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR

OFF 50 FT ROLL 50 FT OBS ROLL 50 FT OBS ROl.L 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS

1670 50 54 S.L. 640 1190 695 1290 755 1390 810 1495 875 16051000 705 1310 765 1420 825 1530 890 1645 960 17702000 775 1445 840 1565 910 1690 980 1820 1055 19603000 855 1600 925 1730

I1870 1080 2020 1165 2185

4000 940 1775 1020 1920 2080 1190 2250 1285 24405000 1040 1970 1125 2140 [215 2320 1315 2525 1420 27506000 1145 2200 1245 2395 1340' 2610 1455 2855 1570 31257000 1270 2470 1375 2705 1490 2960 1615 3255 1745 35908000 1405 2800 1525 3080 1655 3395 1795 3765 1940 4195


CESSNAMODEL 152

RATE OF CLIMB

I MAXIMUM!CONDITIONS

Flaps UpFull Throttle

NOTE:Mixture leaned above 3000 feet for maximum RPM.

Figure 5-5. Rate of Climb

5-12

WEIGHTPRESS CLIMB RATE OF CLIMB - FPM

LBSALT SPEEDFT KIAS -20°C ooc 20°C 40°C

1670 S.L. 67 835 765 700 6302000 66 735 670 600 5354000 65 635 570 505 4456000 63 535 475 415 3558000 62 440 380 320 265

10,000 61 340 285 230 17512,000 60 245 190 135 85

CESSNAMODEL 152


TIME, FUEL, AND DISTANCE TO CLIMB

IMAXIMUM RATE OF CLiMBI

CONDITIONS:Flaps UpFull ThrottleStandard Temperature

NOTES:1. Add 0.8 of a gallon of fuel for engine start, taxi and takeoff allowance.2. Mixture leanedabove 3000 feet for maximum RPM.3. Increasetime, fuel and distance by 10%for each 1QoCabove standard temperature.4. Distancesshown are basedon zero wind.

Figure 5-6. Time. Fuel. and Distance to Climb

5-13

PRESSURE CLIMB RATE OF\ FROM SEA LEVELWEIGHT

ALTITUDETEMP

SPEED CLIMBLBS

FT°c KIAS FPM TIME FUEL USED DISTANCE

MIN GALLONS NM

1670 S.L. 15 67 715 0 0 0

1000 13 66 675 1 0.2 2

2000 11 66 630 3 0.4 3

3000 9 65 590 5 0.7 5

4000 7 65 550 6 0.9 7

5000 5 64 505 8 1.2 9

6000 3 63 465 10 1.4 12

7000 1 63 425 13 1.7 14

8000 -1 62 380 15 2.0 17

9000 -3 62 340 18 2.3 21

10,000 -5 61 300 21 2.6 25

11,000 -7 61 255 25 3.0 29

12,000 -9 60 215 29 3.4 34


CESSNAMODEL 152

CRUISE PERFORMANCE

s-r 1-'0rL 5 5 ~ ~

")L.I '-

CONDITIONS:1670 Pounds

Recommended Lean Mixture (See Section 4, Cruise)

NOTE:Cruise speeds are shown for an airplane equipped with speed fairings which increase the speedsby approximately two knots.

Figure 5-7. Cruise Performance

5-14

20°C BELOW STANDARD 20°C ABOVEPRESSURE STANDARD TEMP TEMPERATURE STANDf.-RD TEMPALTITUDE RPM

FT % KTAS GPH% KTAS GPH

% KTAS GPHBHP BHP BHP

2000 2400 - - - - - -. - - - 75 101 6.1 70 101 5.72300 71 97 5.7 66 96 5.4 63 95 5.12200 62 92 5.1 59 91 4.8 56 90 4.62100 55 87 4.5 53 86 4.3 51 85 4.22000 t 49 81 4.1 47 80 3.9 46 79 3.8

4000 2450 - - - - - - - - - 75 / 6.1 70 102 5.72400 76 102 6.1 71 01 517 67 100 - 5.42300 67 96 5.4 63 5.1 60 95 \ 4.92200 60 91 4.8 56 90 4.6 54 89 4.42100 53 86 4.4 51 85 4.2 49 84 4.02000 48 81 3.9 46 80 3.8 45 78 3.7

\6000 2500 - - - - - - - - - 75 105 6.1 71 104" 5.7

2400 72 101 5.8 67 100 5.4 64 99 5.22300 64 96 5.2 60 95 4.9 57 94 4.72200 57 90 4.6 54 89 4.4 52 88 4.32100 51 85 4.2 49 84 4.0 48 83 3.92000. 46 80 3.8 45 79 3.7 44 77 3.6

8000 2550 - - - - - - - - - 75 107 6.1 71 106 5.72500 76 105 6.2 71 104 5.8 67 103 5.42400 68 100 5.5 64 99 5.2 61 98 4.92300 61 95 5.0 58 94 4.7 55 93 4.52200 55 90 4.5 52 89 4.3 51 87 4.22100 49 84 4.1 48 83 3.9 46 82 3.8

10,000 2500 72 105 5.8 68 103 5.5 64 103 5.22400 65 99 5.3 61 98 5.0 58 97 4.82300 58 94 4.7 56 93 4.5 53 92 4.42200 53 89 4.3 51 88 4.2 49 86 4.02100 48 83 4.0 46 82 3.9 45 81 3.8

12,000 2450 65 101 5.3 62 100 5.0 59 99 4.82400 62 99 5.0 59 97 its 56 96 4.62300 56 93 4.6 54 92 4.4 52 91 4.32200 I 51 88 4.2 49 87 4.1 48 85 4.02100 I 47 82 3.9 45 81 3.8 44 79 3.7

CESSNAMODEL 152


RANGE PROFILE45 MINUTES RESERVE

24.5 GALLONS USABLE FUEL

CONDITIONS.1670 PoundsRecommended Lean Mixture for CruiseStandard TemperatureZero Wind

NOTES:1. This chart allows for the fuel used for engine start, taxi, takeoff and climb, and the

distance during climb as shown in figure 5-6.2. Reserve fuel is based on 45 minutes at 45% BHP and is 2.8 gallons.3. Performance is shown for an airplane equipped with speed fairings which increase

the cruise speeds by approximately two knots.

I l.ti '\!N80'KTASIf' '194 KTAS

~ " ...1102IdAS./.;.,-.J

~IIll:.

107 KTAS./ 79 KTAS100 KTAS 91 KTAS

197 KTAS - 89 KTAS-f--103 KTA~ I 78 KTAS_f--I a: a:_a: a:w w w w

3: 3: -3: ==0 0 0 0

I a.. a.. - a.. -D.."* ~ ,-"* -rF.

-\00 ;!! ~- U) 87 :g -~-KTAS~ KTAS KTAS~ I /77 KTAS--

S.L.300 350 400 450RANGE- NAUTICAL MILES

Figure 5-8. Range Profile (Sheet 1 of 2)

5-15

12,000

10,000

I- 8000wWLL..Wa 6000=>I-i=...J«

4000

2000

CESSNAMODEL 152


ENDURANCE PROFILE45 MINUTES RESERVE


CONDITIONS:1670 Pounds -Recommended Lean Mixture for CruiseStandard Temperature


time during climb as shown in figure 5-6.2. Reserve fuel is based on 45 minutes at 45% BHP and is 2.8 gallons.

I \1

t

II

I

a:

u

a: a:

ma:

ilJ.J lJ.J W W

~.~ ~ i~ -0 +-0 0 0c.. . c.. c.. c.. .6"", ""

.'. #

.L!"> L!"> L!"> L!">r-- to L!"> <:t ,

2000

S.L.3

t4 5

ENDURANCE - HOURS

6

Figure 5-9. Endurance Profile (Sheet 1 of 2)

5-17

12,000

10,000

I- 8000lJ.JlJ.Ju..

lJ.J 60000.::>I-i=....J« 4000


CESSNAMODEL 152

RANGE PROFILE45 MINUTES RESERVE


CONDITIONS:1670 PoundsRecommended Lean Mixture for CruiseStandard TemperatureZero Wind

NOTES:1. This chart allows for the fuel used for enginestart, taxi, takeoff and climb, and the

distance during climb as shown in figure 5-6.2. Reserve fuel is based on 45 minutes at 45% BHP and is 2.8 gallons.3. Performance is shown for an a'irplane equipped with speed fairings which increase

the cruise speeds by approximately two knots.

~ 80+-t--, KTAS..+-+i 94 rl-

KTASI-+

1-+--107 ~100KT AS-I-J.-KT AS

t 79 t-+-KTASt---+-i I

S.L.550 600 650 700

RANGE - NAUTlf:AL MILES750

Figure 5-8. Range Profile (Sheet 2 of 2)

5-16

12,000

10,000

f- 8000wwu.

w60000

:Jf-f-...J

4000

LANDING DISTANCE

I SHORT FIELD I

CONDITIONS:Flaps 30°Power OffMaximum BrakingPaved, Level, Dry RunwayZero Wind,

NOTES:1. Short field technique as specified in Section 4.2. Decreasedistances 10% for each 9 knots headwind. For operation with tailwinds up to 10 knots, increase distances by

10% for each 2 knots.3. For operation on a dry, grass runway, increase distances by 45% of the "ground roll" figure.

'f....co--Cilroacr'.......po:J

~ Figure 5-10. Landing Distance

~oOt;jtJoot;jOOt"'Z>CJ1ro

""dt;j

~000:;ct;j~O>:jZOoZt;jCJ1

SPEED OOC 1QoC 20°C 30°C 40°C

WEIGHT AT PRESS

LBS 50 FT ALT TOTAL TOTAL TOTAL TOTAL TOTAL

KIAS FT GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEARROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS

1670 54 S.L. 450 1160 465 1185 485 1215 500 1240 515 12651000 465 1185 485 1215 500 1240 520 1270 535 12952000 485 1215 500 1240 520 1270 535 1300 555 1330

3000/ 500 1240 520 1275 540 1305 560 1335 575 13604000 520 1275 540 1305 6 1335 580 1370 600 1400

500Q 540 1305 560" 1335 58 1370 600 1400 620 14356000 560 1340 580 1370 605 1410 625 1440 645 14757000 585 1375 605 1410 625 1440 650 1480 670 15158000 605 1410 630 1450 650 1480 675 1520 695 1555


CESSNAMODEL 152

ENDURANCE PROFILE45 MINUTES RESERVE


CONDITIONS:1670Recommended Lean Mixture for Cruise

Standard Temperature


time during climb as shown in figure 5-6.2. Reserve fuel is based on 45 minutes at 45% BHP and is 2.8 gallons.

5-18

S.L.5 6 7 8

ENDURANCE - HOURS

9 10

Figure 5-9. Endurance Profile (Sheet 2 of 2)

12,000

10,000

f- 8000wwu.

w60000

::>f-f-...J<{ 4000

2000

I I I [ I '<Jl I I 1.1 I I I I

W-t-- I ! -',," , . Ii I! . , I I, ;

! i; "'-1,' I', I I ' ,1,

I ! ! '<PI i i i i , : i : f I

H=+I,,I ! ' ,I: i "

P-i;/ ' i

--+-1'<..':::;j"/1 . i! i! ' I

[ !:l I iI . I : ! :

I i : I, i ' I, Ii. , : ,I ' ! i'II ' I I 1,

i 'I ! I I ! , 1Ii I i:, I I, II i i ' I " , I '1 i i i : i : i :

! i' i ' I Ii.

f-+-; b=-' " i I '11 i

=t- i a:1 a: "T i

w uJ

t+ -3 "3 3 I I ' ,1-+-°

P=f-2 °II i o ! i '

rc... c...

*-oli ' I *- 11

d" -rd"I£) r+- I£) II£) i I£) ii.... co 1-'-

I£) .q1"1i

! i I I ,. ;1 I I I, I I I. ,

........~.....'<....co~00

0)

-b Figure 6-6. Sample Loading Problem

:::;:0Ot<:!t::Jcnt<:!cnt"'Z>01~

~t<:!......

t<:!QD:I:Q0-:3::a &0:::;:b::1cnt<:!>t<:!Zt"'O0-:3>0-:3

t"'Z80",cnt<:!"'-10-:3--0)

SAMPLE SAMPLE AIRPLANE YOUR AIRPLANE

LOADING PROBLEMMoment Moment

Weight (lb. -ins. Weight (lb. - ins.(Ibs.) /1000) (Ibs.) /1000)

1. Basic Empty Weight (Use the data pertaining to yourairplane as it is presently equipped. Includes unusablefuel and full oil) . 1136 34.0

2. Usable Fuel (At 6 Lbs./Gal.)Standard Tanks (24.5 Gal. Maximum) . . 147 6.2

Long Range Tanks (37.5 Gal. Maximum) .Reduced Fuel (As limited by maximum weight)

3. Pilot and Passenger (Station 33 to 41) 340 13.3

4. * Baggage - Area 1 (Or passenger on child's seat)(Station 50 to 76, 120 Lbs. Max.) . 52 3.3

5. *Baggage - Area 2 (Station 76 to 94, 40 Lbs. Max.)

6. RAMP WEIGHT AND MOMENT / 1675 56.8

7. Fuel allowance for engine start, taxi, and runup -5 -.2

8. TAKEOFF WEIGHT AND MOMENT(Subtract Step 7 from Step 6) 1670 56.6

9. Locate this point (1670 at 56.6) on the Center of Gravity Moment Envelope,and since this point falls within the envelope, the loading is acceptable.

* The maximum allowable combined weight capacity for baggage areas 1 and 2 is 120 pounds.

25

LOAD MOMENT/1O00 (KILOGRAM-MILLIMETERS)

50 75 100 125 150

I-- FUEL ISTANDARD TANKS)

~.,. @ 6../GAL. 10,72 KG/LITRE)

- - BAGGAGEIN AREACD lOR- PASSENGER ON CHILD'S SEAT)

:1. 120.. MAX. 154.4 KG MAX)

.:j BAGGAGEIN AREA@ 40.. MAX.- 11B,1KGMAXI

. 30' (1 13,6)L-U--!--'~

f:iITt

H

l'ltt+H-1 --j-j

!~~t24.5 GAL.

! , r ~92.7 LITRE) MAX20 (75,n

~.

4 6 752 3

r

--1-.!--1

~-'-+'Hl-I+t+H-H-H-!-+++

1

- ,--,i; -;.._,'"," - :'

"-+ II:j-j-j- ~ .

37.5 GAL. (141,9 LITRE) MAXJilJilLllJl1L: ' . , , , , .

.

LOADING GRAPH

8 9 10 12 1311 14

LOAD MOMENT/1O00 (POUND-INCHES)

Line representing adjustable seats shows the pilot or passenger center of gravity on adjustableseats positioned for an average occupant. Refer to the Loading Arrangements Diagram forforward and aft limits of occupant C.G. range.

Figure 6-7. Loading Graph

15

s::00t:jt':!t':!OOt"OO""Z~~

cp....0 0

r400

350

r;;0 300z::>

-:: 250r-:r:

uJ 200?

0<t:0 150-'

100

50

00

.....<-, NOTES::::

....co-.J00

t':!:E;OO175 .ot':!t':!

C::.....O""'Q

200 'i:I:I1"'"s::0t':!goZZ 0)

175 tI1t".....t"OO

150 en Z:2: 0<t: t':!cr: --

125 g-'

100(9w

75 :s:0<t:0-'

50

25

0

.........s::......'<....~""00

1700(j).Clz

is 1600~I-

~ 1500w~w 1400z«-'&: 1300«Cl

~ 1200«0-'

1100

0':>I........

350

LOADED AIRPLANE MOMENT/1O00 (KILOGRAM-MILLIMETERS)

400 450 500 550 600 650 700

CENTER OF GRAVITYMOMENT ENVELOPE

100030 35 40 45 50 55

LOADED AIRPLANE MOMENT/1O00 (POUND-INCHES)

60

Figure 6-8. Center of Gravity Moment Envelope

oOt.:<jt;!OOt.:<jOO

t"'Z....>C11ro

800

E-775 (j):2:

750

725 g-'700 g675

(:J

650 W

625 wz

600 «-'0..

575 a:

550 Clw

525 t.:<jH500 9 t.:<jO

,o:I:475 <::0-,3

::ij&o65 tJ:100

t.:<j>t.:<jZt"'O0-,3>0-,3t"'ZOHOZOOt.:<j0-,3--0':>

... ." .'

. ;(1<8tc!S:'jAircraft I\II~O~0~.rneir1t.::'i"',::'" ,.., ',' J "',"".. .."", ". .,'

',11:~4S. '1640 W.,Hangar 19, ,WQods,Cross,l)T 84087.J ", .. . " . ,.'.' ,..

~'/.

WEIGHT AND, BALAN'CE 'DATA AND RECORD ".',.". .,

AIRCRAFT TYPE

, REGISTRAION#'

ADJUST DATE

( ,

THE BASIC EMPTYWEIGHT OF THE AIRPLANEAS DELIVEREDFROM THE FACTORY,O.RTHE LAST WEIGHT ANDBALANCE ADJUSTMENT, SHOULD BE THE FIRST ENTRY IN THE DATA RECORD. BELOW. THIS FORM IS PROVIDED TOPRESENT THE CURRENT STATUS OF THE AIRPLANE AND A COMPLETE tllSTORY OF PREVIOUS MODIFICATIONS ASSHOWN IN THEAIRCRAFTLOGBOOK. ANYSUBSEQUENT MODIFICATION WHiCH AFFECTS THE WEIGHT ORMOMENTSHOULD BE ENTERED IN THE WEIGHT AND BALANCE RECORD. .;.. . .

'.'

WEIGHT AND BALANCE DATA FORM

. DATE DESCRlt:TION OF MOD ADD SUB .ARM MOMENT LBS.' USEFUL

'.MAXIMUM RAMP WEIGHT

MAXIMUM BAGGAGE

1,670.00

120.00

1,166.50

/ :'.' ..',NEW EMPTY WEIGHT

N~W CG (ARM)

NEW USEFUL LOAD

STANDARD EMPTY WEIGHT

'MAXIMUM STAND,f\RD USEFUL I .. 503.60

, " 'F

; . .iSIGNATURE A&P:,; . '\ ,,",; ,;'. .,

,,. '., '"

, ", '"

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.(lI'l -t,> <$5228.30 503.59,0/29/1988' PREVJO/JS WEIGF'lT 30.2 1166.50. m;.. ..,,..

:. ,. .. ..5.02 . I' ii, !!;j, .,"1 ",",.StE"06/17/2003 Kt:X::135Piw/mounting tray i 15.0

','

". .

,n' .

I..ii. '.' '..GPS htena ". ') 0.27 , 32.0,1:' : 1':'."'-'-":' ",i/"

. ". .""" ',.A:i.:' .;;.' Comm Anten'a 0.50 40.0 .",.""..j ,.: .,,;i<,

. " \"A" "" " ';'Voltage Converter 1.20 5.0: , 6.qO. "

'." \'"

.' ., ,i!J'..,:iP If.,.

, """-'.-.- ., ..."i'">-. .- .,- _. ,_...,..,-,',......... '"-'i!!". "';:"":.2!:I'::'IO;'"" " ,j.. ".

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TOTALS..

6.99 -0.00 30:11 35338.24 1173.49 496.51

117.3.49.. .. .

30.11 '.'

.. 496.51

Documents

AIRSPEED CALIBRATION - Axenty Aviation 152 PD.pdf · 40 -20 a 20 40 60 DEGREES - CELSIUS Figure 5-2. Temperature Conversion Chart 5-9. SECTION 5 PERFORMANCE CESSNA MODEL 152 STALL