CESSNA SECTION 5

MODEL 208 (675 SHP) PERFORMANCE

(

(
( INTRODUCTION
( Performance data charts on the following pages are presented so
that you may know what to expect from the airplane under various
( conditions, and also, to facilitate the planning of flights in detail and
( with reasonable accuracy. The data in the charts has been
computed from actual flight tests using average piloting techniques
( and an airplane and engine in good condition .
(
( A, WARNING
( To ensure 'that performance In this section can
be duplicated, the airplane and engine must be
( maintained . in good condition. Pilot proficiency
( and proper preflight planning using data
necessary for all flight phases Is also required to
( assure expected performance with ample
margins of safety.
(
It should be noted that the performance information presented in the
( ('
....
~ -.~ -
range and endurance profile charts allows for 45 minutes reserve
( fuel at the specified cruise power and altitude. Some indeterminate
variables such as engine and propeller condition, .and air turbulence
( may account for varrations of 10 or more in range and endurance.
Therefore, it is important to utilize all available information to
( estimate the fuel required for the particular flight.
(
Notes have been provided on various graphs and ' tables to
(
I approximate performance with the inertial separator in BYPASS
and/or cabin heat on~ The effect will vary, depending upon airspeed,
r temperature, and altitude At lower altitudes, where operation on the
torque limit is possible, the effect of the inertial separator will be
less, depending upon how much power can be recovered after the
separator vanes have been extended.

In some cases, performance charts in this section include data for

temperatures which are outside of the operating limits (Figure 5-5).
This data has been included to aid in interpolation.

1 April 199a 5-5

For Training Purposes Only
 SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

USE OF PERFORMANCE CHARTS

Performance data is presented in tabular or graphical form to '
illustrate the effect of different variables. Sufficiently detailed '
information is provided in the tables so that conservative values can
be selected and used to determine the particular performance figure
with reasonable accuracy.

SAMPLE PROBLEM
The following sampfe flight problem utilizes information from the (
various charts to determine the predicted performance data for a (
typical flight of an airplane not equipped with a cargo pod. A similar
calculation can be made for an airplane ' with a cargo pod using (
charts identified as appropriate for this configuration. The following
information is known:

AIRPLANE CONFIGURATION (WITHOUT CARGO POD)

' (
Takeoff weight: 7850 Pounds
Usable fuel: 2224 Pounds

TAKEOFF CONDITIONS (

(
Field pressure altitude: 3500 Feet
Temperature: 16°C (standard + 8°C) (
Wind component: 12 Knot Headwind
Field length: 4000 Feet (

CRUISE CONDITIONS (
(
Total distance: 650 Nautical Miles
Pressure altitude: 11 ,500 Feet . (
Temperature: 8°C
Expected wind enroute: 10 Knot Headwind (

LANDING CONDITIONS

Field pressure altitude: 1500 Feet

Tem~erature : 25°C
Fiel length: 3000 Feet

5-6 1 April 1998

For Training Purposes Only
(

( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( TAKEOFF
(
( c- The Takeoff Distance chart, Figure 5-9, should be consulted,
keeping in mind that the . distances shown are based on the short
field technique . Conservative distances can be established by
( reading the chart at the next higher value of weight, altitude and
( temperature. For example, in this particular sample problem, the
takeoff distance information presented for a weight of 8000
( pounds, pressure altitude of 4000 feet and a temperature of 20°C
( should be used and results in the following:

( Ground roll: 1530 Feet

Total distance to clear a 50-foot obstacle: 2655 Feet
(
( These distances are well within the available takeoff field length.
However, a correction for the effect of wind may be made based on
( Note 2 of the takeoff chart. The correction fora 12 knot headwind
( is:
( 12 Knots
11 Knots X 10% = 11 % Decrease
(
( This results in the following distances, corrected for wind:
( Ground roll, zero wind: 1530 Feet
( Decrease in ground roll
(1530 feet X 11%): 168 Feet I
(
Corrected ground roll: 1362 Feet
(
( Total distance to clear a
50-foot obstacle, zero wind: 2655 Feet
( Decrease in total distance
( (2655 feet X 11 %): 292 Feet I
Corrected total distance
( to clear a 50-foot obstacle: 2363 Feet
(
The Engine Torque For Takeoff chart, Figure 5-8, should be

( (~!'
consulted for takeoff power setting. For the above ambient
(
conditions, the power setting is:

Takeoff torque : 1865 Ft-Lbs

7 September 2001 5-7

For Training Purposes Only
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

CRUISE

The cruising altitude should be selected based on a consideration of

trip length, winds aloft, and the airplane's performance. A cruising .
altitude and the expected wind enroute have been given for this !.

sample problem. However, the power setting selection for cruise

must be determined based on several considerations. These include
the cruise performance characteristics presented in Figure 5-19, the
Fuel And Time Required charts presented in Figures 5-20 and 5-21,
the Range Profile chart presented in Figure 5-22, and the
Endurance Profile chart presented in Figure 5-23.

The Range Profile chart, Figure 5-22, shows range at maximum

cruise power and also . at maximum range power. For this sample
problem, maximum cruise power and 1900 RPM will be used.

The Cruise Performance chart for 12,000 feet pressure altitude is

entered using 10°C temperature. These values most nearly (
correspond to the planned altitude and expected temperature (
conditions. The torque setting for maximum cruise power is 1291 Ft-
Lbs torque at 1900 RPM which results in the following: .

True airspeed: 173 Knots

Cruise fuel flow: 306 PPH

FUEL REQUIRED

The total fuel requirement for the flight may be estimated using the
performance information in Figures 5-18, 5-19 and 5-24 or in
Figures 5-.20 and 5-21 . The longer detailed method will be used for
this sample problem, but the use of Figures 5-20 and 5-21 will
provide the desired information for most flight planning purposes.

Assuming a maximum climb, Figure 5-18 may be used to determine

the time, fuel and distance to climb by reading values for a weight .(
of 8000 pounds and a temperature 20°C above standard. The
difference between the values shown in the table for 4000 feet and (
12,000 feet results in the following:

Time : 10 Minutes
Fuel: 60 Pounds
Distance : 20 Nautical Miles

5-8 1 April 1998

For Training Purposes Only
(
( CESSNA SECTION 5
MODEL 20a (675 SHP) PERFORMANCE
(
(
Similarly, Figure 5-24 shows that a descent from 12,000 feet to sea
( level results in the following:
(
Time 15 Minutes
(
( Fuel 65 Pounds
( Distance 43 Nautical Miles
(
The distances shown on the climb and descent charts are for zero
( wind. A correction for the effect of wind may be made as follows:
( Distance during climb with no wind 20
(
Decrease in distance due to wind
( (10/60 X 10 knot headwind) 02
(
Corrected distance to climb: 18 n.m.
(
Similarly, the distance for descent may be corrected for the effect
( of wind and results in 40 nautical miles
(
The cruise distance is then determined by subtracting the distance
( during climb and distance during descent.
(
Total distance 650
(
(
Distance during climb and descent -58

( Cruise distance 592 Nautical Miles

(
(
(

(
(
(.»
(
(

1 April 199a
For Traininl! Purposes Only
 (
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP) (

With an expected 10 knot headwind, the ground speed for cruise is

predicted to be:

173
(
:1Q (
163 Knots (
Therefore, the time required for the cruise portion of the trip is:

590 Nautical Miles

163 Knots = 3.6 Hours

The fuel ,required for cruise is:

3.6 hours X 306 pounds/hour = 1102 Pounds

A 45-minute reserve requires:

45
60 X 306 pounds/hour = 230 Pounds

The total estimated fuel required is as follows:

Engine start, taxi, and takeoff 35

Climb 60

Cruise 1102

Descent 65

Reserve 230
(
Total fuel required (pounds) 1492
(
Once the flight is underway, ground speed checks will provide ' a
(
more accurate basis for estimating the time enroute and the
corresponding fuel required to complete the trip with ample reserve. (

5-10 1 Apri11998
For Training Purposes Only
 (

( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( LANDING

A procedure similar to takeoff should be used for estimating the

(~ .
( " . landing distance at the destination airport. The estimated landing
-'. '~ ; weight is as follows :
(

( Takeoff weight 7850

( Fuel required for climb,

cruise, and descent 1262
(
( Landing weight 6588 Pounds
( Figure 5-25 presents landing distance information for the short field
( technique. The landing distances for a weight of 6800 pounds and
corresponding to 2000 feet pressure altitude and a temperature of
( 30°C should be used and are as follows: .
(
Ground roll 700 Feet
(

( ( -': ":"-.-' .
Total distance to clear a 50-foot obstacle 1585 Feet

( A correction for the effect of wind may be made based on Note 2 of

the landing chart using the same procedure as outlined for takeoff.
(
(
(
(

(
(

(
(

(
(
C"
. ~~;•.> '.;;I.'~ '

,(

1 April 1998 5-11

For Training Purposes Only
 CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE

(
ISA CONVERSION
AND OPERATING TEMPERATURE LIMITS
(
/" -
( f

(
'(

A. CAUTION
Do not Operate In shaded area of chart.
(
(

30

25
(

(
Ii:
o .
( g 20 .

(
UJ
( ( 0
:J
t:: 15
( ~
~
UJ
( a::
:J
Ul
Ul
( ~ 10
Il.

5
(

0
-70 ·60 -50 -40 -30 -20 -10 0 10 20 30 40
OUTSIDE AIR TEMPERATURE _·c

2685T1010

Figure 5-5. ISA Conversion and Operating Temperature Limits

1 April 1998 5-17

For Training Purposes Only
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

STALL SPEEDS AT 8000 POUNDS

Conditions:
Power Lever - Idle
Fuel Condition Lever- High Idle

MOST REARWARD CENTER OF GRAVITY

ANGLE OF BANK
FLAP 45°
SETTING 0° 30° 60°
KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS
UP 63 75 68 81 75 89 89 106
10° 60 66 64 71 71 78 85 93
20 56 62 60 67 67 74 79 88
30 0
50 61 54 66 59 73 71 86

MOST FORWARD CENTER OF GRAVITY

ANGLE OF BANK
FLAP 45
SETTING 0
0
300 0
60 0
KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS
UP 63 75 68 81 75 89 89 106
10 0
61 67 66 72 73 80 86 95
20 57 63 61 68 68 75 81 89
30° 50 61 54 66 S9 73 71 86

NOTES:

1. Altitude loss during a stall recovery may be as much as 300 feet

from awings-Ievel stall and even greater from a turning stall.

2. KIAS values are approximate .

Figure 5-6 _ Stall Speeds

5-18 1 April 1998

For Training Purposes Only
 (

( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( WIND COMPONENTS
NOTE: Maximum demonstrated crosswind velocity is 20 knots
( (not a limitation).
(

rn
t-
oZ
~
,
>-
~
Z
30 ~,
,,, " ,."'"' ' [I
( ::::l :~-l--
a: i :. i;
( ~
...J
W
( ...J
...J

( ~
0:
I-
( Z
W ~ ,"'0
Z
( 0
c.. I· . • .

:E 10
( 0
u
0
( z
?; '.i'
( . ._~ : i !' , ~O
0

! '
: i
:~
( ,¥ ' ! '1'<rJ .••
-10 -'"
0 10 20 30 40 50
CROSSWIND COMPONENT - KNOTS

5584T7021
Figure 5-7. Wind Components

1 April 1998 5-19

For Training Purposes Only
 (
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP) (

(
ENGINE TORQUE FOR TAKEOFF
CONDITIONS:
1900 RPM
60 KIAS
Inertial Separator - Normal

NOTES:
1. Torque increases approximately 10 Ft~Lbs from 0 to 60 KIAS.
2. Torque on this chart shall be achieved without exceeding
805°C ITT or 101.6 percent N g . When the ITT exceeds 765°C,
this power setting is time limited to 5 minutes.
3. W ith the inertial separator in BYPASS and takeoff power set
below the torque limit (1865 Ft-lbs), decrease torque setting by
15 Ft-Lbs.
4 ; With the cabin heater on and takeoff power set below the
torque limit (1865 Ft-Lbs), decrease torque setting by 65 Ft-Lbs.

2000

1900 TOROU LlMI T • 1865 FT-LB5

~
IBOO ,., 1.<::
U1 '%~S1 ... 1;;
CD
,
....J \S'c., ~

t 1700 :?(C'
'5k /'/ d'
UJ /'(.,
e:>. ;§
~ 1500
If"
/0
,
C>
I- /0 {.> i:::
°0 ~
1500 A'/ , rY?
C:l

~
~

1400

130~.m -20 - 10 0 10 20 30 40 50 60
OUTS IDE AIR TEMPERATURE - 'C
2685T1011
Figure 5-8. Engine Torque for Takeoff

5-20 1 Apri l 1998

For Training Purposes Only
 (

( C.ESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE

( CARGO POD INSTALLED

TAKEOFF DISTANCE
( (GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
( ( CONDITIONS:
SHORT FIELD
NOTES :
FLAPS 20 DEGREES 1 USE SHORT FIELD TECHNIQUES AS SPECIFIED IN SECTION 4 .
( 1900 RPM 2. DECREASE DISTANCES 10% FOR EACH 11 KNOTS HEADWIND. FOR
INERTIAL SEPARATOR· NORMAL OPERATION WITH TAILWINDS UP TO 10 KNOTS. INCREASE DISTANCES BY 1(1%
CABIN HEAT · OFF FOR EACH 2 KNOTS .
( TORQUE SET PER FIGURE 5·8 3. FOR OPERATION ON A DRY, GRASS RUNWAY, INCREASE .DISTANCES BY 15%
PAVED. lEVEL. DRY RUNWAY OF THE -GROUND ROLL' FIGURE.
ZERO WIND 4. WITH TAKEOFF ' POWER SET BELOW THE TORQUE LIMIT (1865 FT·LBS).
INCREASE DISTANCE (BOTH GROUND ROLL AND TOTAL DISTANCE) BY 3% FOR
INERTIAL SEPARATOR IN BYPASS AND INCREASE GROUND ROLL 5% AND
( TOTAL DISTANCES 10% FOR CABIN HEATON.
5. WHERE DISTANCE VALUES HAVE BEEN REPLACED BY DASHES, OPERATlM3
TEMPER ATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED.
THOSE DISTANCES WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY
EXCEEDS THE TEMPERATURE LIMIT ARE PROVIDED FOR INTERPOLATION
PURPOSES ONLY
6, FOR OPERATIONS ABOVE 40"C AND BELOW THE TEMPERATURE OPERATING
LIMITATIONS. MULTIPLY TAKEOFF DISTANCES AT 40' C BY 1.2.
I
(
WI I ~~~~~r RESS -10'C O'C 10'C 20'C 30'C 40'C

~~~L ~~Hl '¥~AL

LE KIAS '~~HL oRu II~~AL CWU l'OIRl
~~~L ~~~L ~~~L
AL T I,O,AL
( Al FT I TO ROLL TO
b~~
ROLL
50 F FT 50 FT FT 50 FT rr 50 FT FT SO FT fT 50 FT FT 50 fl
( 8 72 82 SL 1010 1820 1010 1925 1135 2035 1205 2145 1215 2260 1345 2380
~, ~~~
0 1000 1070 1925 1135 2035 1205 2150 1280 2270 1355 1445 2550
0 200C 1135 2035 1210 2155 1285 2275 1360 2405 1~~0 1570 2180
( 0 3000 1205 2150 1285 2280 1365 2415 1450 2550 1535 2690 1105 3035

( i' ~~g~ ~m ~~~~ 1~~~ ~~~~ ~~~~

6000 1460 2570 1555 2725 1655
mg
2890
~~:~ ;~~~ 1~;g
1755
11~
3065 1915
~~70
3500
<15 ~~~~
3320
3640
2240 4010
\"
~~gg 1555
I~~n ]: 1660
_1775 ~m
1765
1 ~I 0 ~~~g
1940
7150 i~~g
3925
~~~~ 44'1n
2495 4615
---- ----
9000 1775 3100 1900 3300 2115 3125 2390 4295 2115 5035 ---- --_.
l~~gg ~~~~ i~~~
3660
~~~~ <1120 ~~~~
4180
~~~~
4865 3040 5175 ---- ----
----
<17<10 5510 3il15 6730 -- --'
( 1 10 BO
200
SL
2310
860
4070
1545
2595 4665
915 1635
2930
970
5415
1725
3345
1025
6445
1815
3855 7995
1085 1915
----
1145
---.
2010
5
0
0
~~gg ~.1O
3000
70
1030
1635
lJ25
1820
910 1725
1030 1825
1095 1930
~g~~ m~ ~~~~
1160 2040 1230
mg
2150
2025
}~~~ 21110
1305 2270
g~~
1450 2550
2155
?34

1515
m~ ~~~~
4000 1095 1930 1165 2045 1235 2160 1310 1390 2415
( 5000 HS5 2045 1240 2165 1315 2295 1395 1515 2S110 1715
6000 1240 2165 1320 2300 1405 2435 1490 2515 1670 2925 1890 3375
1000
BOOU
9000
1320
1410
1510
2300
2445
2605
1410 ' 2445
1505 2600
1610 2770
mg
1790
2590
'195
3110
}~~~ ~~:~ ~~;g ~~~~ ---- ----
2015 3560 2280 4125
2100 3795

---- - ---
~~j8
1770
;~~; ~~i~ ~~~~ :~~~ ~~~~
4680 ---- - -- -
19S:; ~~;~
DODO 1615
IIOOC 1760 5365 --- - ----
2000 3390
1950 21B5 3855 2460 4425 2195 5115 3205 6215 ---- ----
1 67 77 SL 1305
730 175 1380 820 1455 870 1530 915 1610 910 1690
915 1100 1040
~~~ i~~~
0 1000 115
1375 820 1455 870 1535 1615
0 200e 1450
820 870 1535 925 1&20 1105 1035 1795 1125
0 3000 1535
810 925 1620 985 1110 10<10 1805 1100 1900 1220 2125
4000
500t m
1620
.1715
6000 1050 1820
1~~~
1115
1 A15
1115 1925
1045
1115
lI85
1815
1920
2040
1110
1180
1260
1915
2030
2155
1115 20Z5
1280 2205
1410 2435
1325 2310
1440 2515
1590 2185
~~~~
1760 3115
~~~~ i~~~10 m~
7000 1930 1190 2045 1265 1555
BoDe ~~~~
2050 1210 2115 1365 1~ 1720 ~--- - --.
9000 1215 2180 1360 2315 1510 25B5 1690 2940 1910 3375 ---- ----
l~~g~ 1480
1360
mg 1495 2550 1665
m~ ~~~~
3285 ---- ----
m~ ~~~g ---- ----
1655 2840 1850 1"~"
2000 1640 2810 1835 3175 2060 3615 2330 4180 2655 4920 ---- ----

Figure 5-26. Takeoff Distance - Short Field

Revision 6 5-53

For Traininp Pnrnnses Onlv

SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

CARGO POD INSTALLED

TAKEOFF DISTANCE
(GROUND RDLL DISTANCE AND TOTAL DISTANCE TD CLEAR 50 FEET)
FLAPS UP
COND IT IONS, NOTES:
FLAPS 0 DEGREES 1. USE TYPE II OR TYPE IV ANIT-ICE FLUID TAKEOFF
1900 RPM TECHNIDUES AS SPECIFIED IN SECTION 4.
I NERTf AL SEPARATOR - NORMAL 2. DECREASE OISTANCES 10% FOR EACH 11 KNOTS HEADWINO.
CRB I N HEAT - OFF FOR OPERATIONNITH TAILWINDS UP TO 10 KNOTS.
TDROUE SET PER FIGURE 5-8 INCREASE 0 IS TANCES BY lOY. FOR EACH 2 KNOTS.
PRVED. LEVEl. DRY RUNHAY 3. FOR OPERATION ON A DRY. GRASS RUNIIAY. INCREASE
ZERO WIND DISTANCES BY 15% OF THE "GRDUNO ROLL' FIGURE.
4. WITH TAKEOFF POWER SET BELOW THE TORDUE LIMIT
11865 FT-LBS I. INCREASE DISTANCE IBOTH GROUND ROLL
ANO TOTAL DISTANCE I BY 3Y. FOR INERTIAL ,SEPARATOR
IN BYPASS AND INCREASE GROUND ROLL 5% AND TOTAL
OISTANCE 9% FOR CABIN HEAT ON.
5. WHERE DISTANCE VALUES HAVE BEEN REPLACED BY DASHES
OPERATING TEMPERATURE LIMITS OF THE AIRPLANE WOULD
BE GREATL Y EXCEEDED. THOSE DISTANCES HHICH ARE
INCLUDED BUT THE DPERATION SLIGHTL Y EXCEEDS THE
TEMPERATURE II MIT ARE PRDV IDEO FOR I NTERPDLAT ION
PURPOSES ONL Y.

TAKEOFF
WEIGH SPEED PRESS -2D·C _10· C O·C 10·C
LBS KIAS AU GRD TOTAL GRD TOTAL GRO TOTAL GRO TOTAL
IF AT FT ROLL TO ROLL TO ROLL TO ROLL TO
FF o F FT 50 FT FT 50 FT FT 50 FT FT 50 FT
8000 B9 104 SL 1535 2720 1630 2875 1730 3035 1830 3195 (
2000 1720 3020 1830 3195 1940 3375 2050 3560
4000 1930 3365 2055 3565 :>180 3765 .2305 3975 (
6000 2175 3760 2315 3985 2455 4220 2605 4455
8000 2455 4220 2615 4475 21BO 4745 ---- ----
lOOOO 2785 4750 2965 5050 3235 5545 ---- ---- (
2000 3200 5455 3545 6125 3945 6955 ---- - _- ..
(
7500 89 104 Sl 1430 2535 1520 2675 1610 2825 1700 2975
2000 1600 2810 1700 2975 1800 3140 1905 3310
400U 1795 '3130 1910 3315 ?O?S ,50S .21A5 3695
6000 2020 3500 2150 3710 2285 3925 2420 4145
8000 2285 3925 2430 4160 2580 4410 ---- ----
LOOOO 12585 4415 2755 4690 3000 5150 ---- ----
2000 2910 5065 3290 5690 3660 6455 ---- .. ---
7000 89 104 SL 1325 2350 1405 2480 1490 2620 1575 2755
2000 1480 2605 1575 2755 1670 2910 1765 3065
4000 1665 2900 1165 3070 1875 3245 1985 3425
i

600n IB70 3240 1990 3435 2110 3630 2235 3835

Il.ll.!BI~~~I!
I 1l~ 1 3630
.' ,,<,. I
122451 3850 12385 4080 1 ____1----I
@~i'l 25(:: I 4340 2775 I 4765 ---- ~
-_.__-1._-- . . I ..._ . .__ __El
. .__ _. _'-1
~lOrJ 1:745 lj095 [3D40 5L~!l p375 ,L:>S05 u

Figure 5-27. Takeoff Distance· Flaps Up

5-54 1 April 1998

For Training Purposes Only

 (
( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED
(
(
RATE OF CLIMB - TAKEOFF FLAP SETTING
FLAPS 20°
( eONO I TIONS:
TAKEOFF POHER
( 1900 RPM
INERTIAL SEPARATOR - NORMAL
( ZERO WIND
NOTESr
( 1. DO NOT EXCEED TORQUE LIMIT FOR TAKEOFF PER ENGINE TORQUE FOR TAKEOFF
CHART. HHEN ITT EXCEEDS 765°C. THIS POHER SETTING IS LIMITED TO
( 5 HINUTES.
( 2. WITH CLIMB POWER SET BELOW THE TORQUE LIMIT. DECREASE RATE OF CL!MB
BY 20 FPM FOR INERTIAL SEPARATOR IN BYPASS AND 45 FPM FOR CABIN
( HEAT ON.
3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. OPERATING
( TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES OF CLIMB WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY EXCEEo~
( THE TEMPERATURE LIMIT ARE PROVIOEO FOR INTERPOLATION PURPOSES ONLY.
PRESS CLIMB RATE OF CLIMB - FPM
( WEIGHT ALT SPEED
LBS FT KIAS -20"C -. l~C O"C 20 C liD C
( BOOO SL 92 lOiS 1065 1055 1030 1010
( 2000 92 1055 1040 1030 1005 930
11000 91 1030 1015 1000 975 830
( 6000 91 1000 9B5 970 940 no
BODO 90 9iO 955 940 805 575
( 10000 BB 935 920 860 660 435
12000 B7 B80 800 710 515 300
( 7500 SL 92 1195 1180 1170 1150 1125
2000 91 11iO 1160 1145 1125 1050
( 1I000 90 11115 1135 1120 1095 9115
6000 90 1120 1105 1090 1060 830
( 8000 88 1085 1070 1055 920 680
10000 87 1050 1035 975 770 535
( 12000 85 995 910 820 620 395
7000 SL 91 1325 1315 1305 1280 1260
2000 90 1300 1290 1280 1255 1180
/1000 89 1280 1265 1255 1225 1070
6000 89 1250 1235 1225 1195 950
8000 87 1220 1205 1190 1045 795
10000 86 1185 1170 1105 890 6115
12000 1130 lOtiO 945 735 tl95
(~/
8t1
(

Figure 5-28. Rate of Climb - Takeoff Flaps Setting

1 April 1998 5-55

For Training Purposes Only
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

CARGO POD INSTALLED

CLIMB GRADIENT - TAKEOFF FLAP SETTING

0
FLAPS 20
(
CONDITIONS:
TAKEOFF PololER (
1900 RPI1
INERTIAL SEPARATOR - NORMAL (
ZERO HIND
NOTES: (
1. DO NOT EXCEED TORQUE LIMIT FOR TAKEOFF PER ENGINE TORQUE FOR TAKEOFF
CHART . IolHEN ITT EXCEEDS 765°C. THIS POHER. SETTING IS LIMITED TO
5 MINUTES.
2. HITH CLIMB POWER SET BELOW THE TOROUE LIMIT. DECREASE RATE OF CLIMB
BY 10 FT/NN FOR INERTIAL SEPARATOR IN BYPASS AND 30 FT/NM FOR CABIN
HEAT ON. (
3. WHERE RATE OF CLII1B VALUES HAVE BEEN REPLACED BY DASHES . nPERAIING
TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES OF CLII1B WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY EXCEED!
THE TEI1PERATURE LIMIT ARE PROVIDED FOR INTERPOLATION PURPOSES ONLY.
PRESS CLlI1B CLIMB GRADIENT - FliNN
WEIGHT ALT SPEED
LBS FT KIAS -20 C - 10 C (loC 20 C 40 C (
8000 SL 77 830 810 785 745 705
785 765 740 700 635 (
2000 76
4000 76 740 720 700 655 550
76 695 675 655 615 465 (
6000
BODO 76 650 630 610 510 370
585 540 410 275 (
10000 76 610
12000 76 555 495 435 315 190
(
7500 SL 74 940 915 890 845 805
2000 74 890 865 845 800 725 (
4000 74 845 820 795 750 640
6000 74 795 '170 745 iDS 550 {
8000 74 745 720 700 595 440
10000 74 700 675 625 4B5 345 (
12000 73 640 580 515 3B5 250
7000 SL 72 1065 1035 1010 960 915 (
2000 n 1010 985 960 910 830
(
4000 72 960 930 905 860 740
6000 n 905 B80 855 810 640
(
8000 n 855 830 805 690 525
10000 '11 800 775 725 575 420
12000 '11 740 670 605 . 465 320
i
' {-~:. : .

(
Figure 5-29. Climb Gradient - Takeoff Flap Setting

5-56 1 April 1998

For Training Purposes Only
 ( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED
(
(
"F'
;t.'
MAXIMUM RATE OF CLIMB
\ FLAPS UP
( CONDITIONS.
1900 RPM
( INERTIAL SEPARATOR - NORMAL
ZERO WINO
( NOTES I
( 1. TORDUE SET AT 1865 FT-LBS OR LESSER VALUE MUST NOT EXCEED MAXIMUM
CLIMB ITT OF 765'C OR NG OF 101.61..
( 2. WITH CLIMB POWER SET BELOW THE TOROUE LIMIT. DECREASE RATE OF CLIMB
BY 3D FPM FOR INERTIAL SEPARATOR IN BYPASS AND 65 FPM FOR CABIN
HEAT ON.
( 3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. AN
( APPRECIABLE RATE OF CLIMB FOR THE WEIGHT SHOWN CANNOT BE EXPECTED
OR OPERATING TEMPERATURE LIHITS OF THE AIRPLANE WOULD BE GREATLY
EXCEEDED. THOSE RRTES OF CLIMB WHICH RRE INCLUDED BUT THE OPERATION
( SLIGHTLY EXCEEDS THE TEMPE~ATURE LIMIT ARE PROVIDED FOR INTER~OlATIO~
PURPOSES ONLY.
(
PRESS CLI MB RATE OF CLIMB - FPM
( WEIGHT All SPEEO
l"
LBS FT KIRS -1I0'C -20'C o C 20'C 40 C
( 8000 SL 107 1220 1205 1190 1170 925
\. 4000 105 1185 1165 1145 1025 645
( BODO 103 1140 1115 1030 735 390
12000 99 lOBO 945 725 460 155
( 16000 95 820 640 430 185 --
(
20000 91 515 345 140 -- --
24000 87 230 65 -- -- --
7500 SL 107 1340 1325 1310 1295 1035
11000 104 1305 12B5 1265 11115 745
( 8000 102 1260 1235 1150 840 480
12000 99 1200 1060 835 555 235
( 16000 94 930 745 530 270 --
20000 90 620 440 230 -- '- -
( 211000 86 325 155 -- -- - -
, 7000 SL
11000
106
104
1475 1465 1450 lil30 1160
14110 1425 1405 1280 850
8000 101 1400 1375 1285 960 575
12000 98 1340 1195 955 660 325
16000 93 1060 860 635 365 55
20000 89 '135 545 325 70 --
24000 85 425 250 35 -- --

Figure 5-30. Maximum Rate of Climb - Flaps Up

1 April 1998 5-57

Fnr TraininlJ Purnoses Onlv
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

CARGO POD INSTALLED

MAXIMUM CLIMB GRADIENT

FLAPS UP
CONDITIONS:
TAKEOFF POHER
1900 RPtI
INERTIAL SEPARATOR - NORMAL
ZERO WIND
NOTES I
1. 00 NOT EXCEED TOROUE LIMIT FOR TRKEoFF PER ENGINE . TOROUE FOR TAKEOFF
CHART. WHEN ITT EXCEEDS 76S·C. THIS POWER SETTING IS LIHITED TO
5 MINUTES.
2. WITH CLIMB POWER SET BELOW THE .TOROUE LIMIT. DECREASE RATE OF CLIMB
BY 10 FT/NM FOR INERTIAL SEPARATOR IN BYPASS AND 40 FTINM FOR CABIN
HEAT ON.
3. WHERE RATE OF CLltlB VALUES ~AVE BEEN REPLACED BY DASHES. OPERATING
TEMPERATURE LltlITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES ofCLIM6 WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY EXCEED~
THE TEMPERATURE LIMIT ARE PROVIDED FOR INTERPOLATION PURPOSES ONLY.
PRESS CLIMB [LIMB GRADIENT - FT/Nt!
WEIGHT ALI SPEED
LBS FT KIAS -20C -10 [ o C 20·C 4()·C
8000 SL 90 800 7BO 760 730 580
2000 90 765 745 725 690 485 ('
4000 90 725 705 690 605 400
6000 89 690 670 650 515 315
8000 89 650 635 585 425 245
10000 88 615 555 490 340 180
12000 88 525 460 400 260 110
7500 SL 89 890 870 850 815 655
2000 88" 855 835 815 775 560
4000 88 815 795 775 6B5 465
6000 87 175 755 735 585 380
8000 87 735 715 665 490 300
10000 86 695 635 560 405 230
12000 86 600 535 4S5 320 160
7000 SL 87 995 975 955 915 745
2000 87 955 935 910 875 640
11000 86 910 890 870 775 5110
6000 86 870 850 830 670 450
8000 85 825 805 750 570 365
10000 B5 785 720 645 475 295
12000 84 680 615 540 385 215

Figure 5-31. Maximum Climb Gradient - Flaps Up.

5-58 1 April 1998

For Training Purposes Only
 (

( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED
(
/- - CRUISE CLIMB
( { FlRPS UP
CONOI TIONS:
( 1900 RPM
INERTIAL SEPARATOR - NORMRL
( ZERO WINO
( NOTES.
1. TORQUE SET AT 1865 FT-lBS OR lESSER VALUE MUST NOT EXCEED MAXIMUM
( CLIMB ITT OF 76S·C OR NG OF 101.6r..
2. WITH CLIMB POWER SET BELOW THE TORQUE LIMIT. DECREASE RATE OF CLIMB
( BY 50 FPM FOR INERTIAL SEPARATOR IN BYPASS AND 70 FPM FOR CABIN
HERT ON.
( 3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. AN
APPRECIABLE RATE OF CLIMB FOR THE WEIGHT SHOWN CANNOT BE EXPECTED
( OR OPERATING TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY
EXCEEDED. THOSE RRTES OF CLIMB WHICH ARE INCLUDED BUT THE OPERATION
( SLIGHTLY EXCEEDS THE TEMPERRTURE LIMIT ARE PROVIDED FOR INTERPOLATIO~
PURPOSES ONLY.
( PRESS CLIMB RATE OF CLIMB - FPM
WEIGHT RLT SPEED
( LBS FT KIAS -<10"C -zo C o C 20 C 40 C
j-
( 8000 SL 120 1190 1165 1140 1115 650
~."<.. , 2000 120 1165 1140 1115 965 495
( 4000 120 1140 1110 1080 800 3<10
6000 120 1110 1080 1025 630 180
( 8000 120 1080 1045 830 445 10
10000 120 1045 955 635 265 --
( 12000 120 1005 755 440 90 --
7500 SL 120 1305 1280 1255 1230 735
( 2000 120 1280 1255 1225 1075 570
~lOOO 120 1255 1225 1195 900 1105
( 6000 120 1225 1195 11110 715 - 235
8000 120 1195 1155 930 520 60
( 10000 120 1155 1060 725 330 --
12000 120 1115 850 520 145 --
( 7000 SL 120 1435 1405 1385 1355 830
2000 120 1410 1380 1355 1190 655
( 11000 120 1380 1350 1320 1005 1180
,/ 6000 120 1355 1320 1265 810 300
8000 120 1320 1280 1040 - 605 110
10000 120 1280 1180 825 400 --
12000 120 1240 955 605 205 --

Figure 5-32. Cruise Climb - Flaps Up

1 April 1998 5-59

For Training Purposes Only
SECTION 5 CESSNA (
PERFORMANCE MODEL 208 (675 SHP) (

(
CARGO POD INSTALLED

RATE OF CLIMB - BALKED LANDING

0
FLAPS 30
COND IT IONS:
TAKEOFF POWER
1900 RPM
INERTIAL SEPARATOR - NORMAL
ZERO WIND
NOTES:
1 . DO NOT EXCEED TORQUE LIMIT FOR TAKEOFF PER ENGINE TOROUE FOR TAKEOFF
CHART. WHEN ITT -EXCEEDS 765"C. THIS POWER SETTING IS LIMITED TO
5 MINUTES .
2 . WITH CLIMB POWER SET BELOW THE TOROUE LI~IT. DECREASE RATE OF CLIMB
BY 15 FPM FOR INERTIAL SEPARATOR IN BYPASS AND 45 FPM FOR CABIN
HEAT ON.
3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. OPERATING
TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES OF CLIMB WHICH ARE INCLUDED BUT TH~ OPERATION SLIGHTLY EXCEED!
THE TEMPERATURE LIMIT ARE PROVIDED FOR INTERPOLATION PURPOSES ONLY.
PRESS CLIMB RATE OF CLIMB - FPM
WEIGHT ALT SPEED
LBS FT KIAS -20 C -10 C O°C 2O·C 40·e
7800 Sl 85 990 980 970 945 920
2000 84 970 955 940 915 B45
4000 B4 940 925 910 BB5 745
6000 83 910 895 880 850 640
BODO B2 880 860 845 715 500
10000 81 840 825 765 580 365
12000 79 785 705 625 440 235
7300 SL 84 1110 1095 1085 1060 1035 (
2000 83 1085 1070 1060 1030 960
4000 83 1055 lOllS 1030 1000 860
6000 83 1030 101.5 1000 965 745
(
BODO 81 995 980 965 B25 600
10000 80 960 9110 880 685 465 (
12000 79 900 820 735 540 330
6800 SL 83 12110 1225 1215 1190 1165 (
2000 83 1215 1200 1190 1165 lOBS
4000 82 1190 1175 1160 1135 985
6000 82 1160 1145 1130 1100 865
BODO BO 1125 1110 1095 955 715
10000 19 1090 1075 10lD 805 570
12000 77 1030 9115 855 655 430

Figure 5-33. Rate of Climb - Balked Landing

5-60 1 April 1998

For Training Purposes Only
CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
CARGO POD INSTALLED

TIME. FUEL. AND DISTANCE TO .CLIMB

HAXIMUM RATE OF CL1HB
CONDITIONS:
FLAPS UP
1900 RPM
INERTIAL SEPARATOR - NORMAL
NOTES:
1. TORQUE SET AT 1865 FT-LBS OR LESSER VALUE MUST NOT EXCEED MAXIMUM
CLIMB ITT OF 765°[ OR NG OF 101.Gr..
2. ADO 35 POUNDS OF FUEL FOR ENGINE START. TAXI. AND TAKEOFF ALLOWANCES.
3. DISTANCES SHDIolNARE BASED ON ZERO !oIINO.
II. IJITH INERTIAL SEPARATOR SET IN BYPASS. INCREASE TIME . FUEL. AND
DISTANCE NUMBERS BY 1% FOR EACH 2000 FEET OF CLIMB AND FOR CABIN
HEAT ON INCREASE TINE. FUEL. AND DISTANCE NUMBERS BY 1% FOR EACH
1000 FEET OF CLIMB .
5. WHERE TIME. FUEL. AND DISTANCE VALUES HAVE BEEN REPLACED BY DASHES.
AN APPRECIABLE RATE OF CLIMB FOR THE WEIGHT SHOWN CANNOT BE EXPECTED .
CLIMB FROM SEA LEVEL
20 DEG ( BELOW STANDARD 20 DEC ( ABOVE
PRESS (LIMB STRNDARD TEI1P TEMPERATURE STANDARD TEMP
WE IGHT All SPEED TIHE FUEL DIST TIME FUEL OIST TIME FUEL DIST
LBS FT K)AS MIN LBS NI1 MIN LBS NH MIN LBS NM
BODO SL 107 0 a 0 0 0 0 0 0 0
lIODO 105 4 25 6 II 26 6 ~ 29 8
8000 103 7 50 12 7 52 13 9 59 17
12000 99 11 76 19 12 80 21 15 94 29
16000 95 15 105 28 17 113 33 24 137 47
20000 91 21 ll10 110 26 156 50 38 202 78
2aooo 87 33 192 62 42 226 83 -- -- - -
7500 SL 107 D 0 0 0 0 O· a 0 0
1I000 lOll 3 22 5 3 23 6 4 26 7
8000 102 6 45 11 7 46 12 B 53 15
12000 99 ID 69 17 10 72 19 13 82 26
16000 94 14 911 25 15 100 29 20 118 110
20000 90 19 124 35 22 136 43 31 167 G2
211000 86 28 165 52 311 186 66 -- -- --
700() SL 106 0 0 0 0 0 0 0 0 0
1I000 104 3 20 5 3 21 5 3 23 6
8000 101 6 41 10 6 42 10 7 <!I 7 13
12000 98 3 62 15 9 611 17 12 73 22
11)000 93 12 85 22 III 89 25 18 102 311
20000 89 17 111 31 19 119 37 26 1111 52
211000 85 24 1114 illl 28 157 55 1I2 202 85

Figure 5-34. Time, Fuel and Distance to Climb - Max Rate

1 April 1998 5-61

For Training Purooses Onlv
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP) (

(
CARGO POD INSTALLED
(

TIME. FUEL. AND DISTANCE TO CLIMB I

CRUISE CLIMB
CONDITIONS:
FLAPS UP
1900 RPM
INERTIAL SEPARATOR - NORMAL
NOTES·
, 1. TORDUE SET ' AT 1865 FT-L8S OR LESSER VALUE MUST NOT EXCEED MRXIMUM
CLIMB ITT OF 76SoC OR NG OF 101.6~.
2. ADD 35 POUNDS OF fUEL FOR ENGINE START. TAXI. AND TAKEOFF ALLOWANCES .
3. DISTANCES SHOWN ARE BASED ON ZERO WIND.
4. WITH INERTIAL SEPARATOR SET IN BYPASS OR CABIN HEAT ON INCREASE
TIME. FUEL. AND DISTANCE NUMBERS BY 1% FOR EACH 1000 FEET OF CLIMB.
CLIMB FROM SEA LEVEL
20 DEG C BELOW STANDARD 20 OEG ( ABOVE
PRESS CLIMB STANDARD TEHP TEMPERATURE STANDARD TEMP
WE IGHT All SPEED T[ME fUEL O[ST lIME FUEL DIST TIME FUEL DIST
LBS FT KIAS MIN LBS NM MIN LBS NM MIN LBS NH
BODO SL 120 0 0 0 0 0 0 0 0 0
2000 120 2 13 4 2 13 II 3 18 6
4000 120 4 26 1 4 27 8 6 31 12
6000 120 6 39 11 6 41 12 9 51 19
BoOO 120 7 53 15 8 56 17 13 80 28
10000 120 9 66 19 11 12 23 18 10i 40
12000 120 12 81 24 1.4 91 30 25 143 57
7500 SL 120 0 0 0 0 0 0 0 0 0
2000 120 2 12 3 2 12 3 3 16 5
4000 120 3 24 6 3 24 7 5 32 11
6000 120 5 35 10 5 37 11 8 50 17
8000 120 7 48 13 7 50 15 12 70 25
10000 120 8 60 17 10 65 20 16 93 35
12000 120 10 73 22 12 82 27 21 122 49
7000 SL 120 a 0 0 0 0 0 0 0 0
2000 120 2 11 3 2 11 3 2 111 5
4000 120 3 21 6 3 22 6 5 29 10
6000 120 5 32 9 5 33 10 7 411 15
8000 120 6 43 12 7 46 14 10 62 22
10000 120 8 54 16 9 59 18 14 82 31
12000 120 9 66 20 11 73 24 18 106 42

Figure 5-35. Time, Fuel and Distance to Climb - Cruise Climb

5-62 1 April1998
For Training Purposes Only
 (
( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED
(
( {
r--
"
( CRUISE PERFORMANCE
( NOTES
(
(
( The following general information is applicable to all Cruise Performance
Charts continued in Figure 36, Sheet 2 through Sheet 13, in this section.
(
1. The highest torque shown for each temperature and RPM
( corresponds to maximum allowable cruise power. Do not exceed
this torque, 740 0 ( ITT, or 101.6% Ng , whichever occurs first.
(
2. The lowest torque shown for each temperature and RPM
( corresponds to the recommended torque setting for best range in
zero wind conditions. .
(
3. With the inertial separator in BYPASSS and power set below the
( torque limit (1865 foot-pounds), decrease the maximum cruise
torque by 100 foot-pounds. Do not exceed 740°C In. Fuel flow for
( a given torque setting will be 15 pph higher.
( 4. With the cabin heat on and power set below the torque limit (1865
foot-pounds), decrease maximum cruise torque by 80 foot-pounds.
( Do not exceed 740 ITT. Fuel flow for a given torque setting will be
0
(

7 pph higher.
(

(
(
(
(
(

Figure ·5-36. Cruise Performance (Sheet 1 of 13)

1 April 1998 5-63

For Training Purposes Only
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

CARGO POD INSTALLED

CRUISE PERFORHANCE
PRESSURE ALTITUDE 2000 FEET .
CONDITIONS.
8000 POUNDS
INERTIRL SEPRRRTOR - NORIIRl
REFER TO SHEET 1 FOR RPPROPRIRTE NOTES RPPLICflBLE TO THIS CHART
TEMP 900 RPM 750 RPM 600 RPM
OEG C TORQUE FUEL TORDUE FUEL TORDUE FUEL
FT -las fLON HAS Fl-lBS FLOW KTRS FT-lBS FLOII KTAS
PPH PPH PPH
45 1252 346 152 1341 346 151 433 346 SO
35 1419 311 162 1579 371 161 1683 371 159
1355 3S9 156 1405 352 153 1500 352 151
1475 349 150
25 1697 409 169 180B 409 168 1920 409 166
1500 378 161 1700 393 164 1800 391 162
1335 353 153 1500 36Z 156 1600 36Z 154
1405 349 151 1465 344 148
15 1865 434 174 1970 431 172 1970 413 166
1700 407 168 1800 405 166 '1800 387 160
1500 316 159 1600 314 158 1600 35~ 153
1345 352 152 1400 345 150 1440 33B 146
1390 344 149
5 1865 431 172 1970 428 110 1910 409 164
1100 404 166 1800 401 164 1800 384 158
1500 373 157 1600 371 157 1600 355 151
1345 349 150 1400 342 148 1430 332 144
1380 339 147
-5 1865 428 170 1910 424 168 1970 404 162
1100 . 401 164 1800 398 163 1800 380 157
1500 310 155 1600 368 155 1600 352 149
1345 346 148 1400 339 147 HIS 321 142
1360 333 145
-15 1865 425 168 1970 420 166 1970 401 160
1700 398 162 1800 394 161 1800 376 ISS
1500 367 154 1600 364 153 1600 348 148
1325 341 146 1400 335 145 1405 322 140
1345 328 142
-25 1865 422 166 1910 411 164 1970 391 159
1700 3S5 160 1800 391 159 1800 373 153
1500 365 152 1600 361 151 1600 345 146
1325 338 144 1400 332 143 1400 318 138
1335 323 140
- 35 1865 420 164 1970 413 162 1910 393 157
1700 393 158 1800 388 157 1800 36~ 151
1500 362 150 1600 358 149 1600 341 144
1325 336 142 1400 329 141 1400 315 136
1350 322 139 1385 313 136
-'IS 1865 419 161 1970 411 160 1970 389 155
1700 391 155 1800 384 154 1800 365 149
1500 360 147 1600 355 147 1600 331 142
1325 334 140 1400 327 139 1400 311 135
1340 118 117 1375 308 134
-54 1865 418 . 159 1970 409 158 1970 386 153
1700 388 153 1800 382 153 1800 362 148
1500 358 146 1600 353 145 1600 334 I'll
1335 333 138 1400 324 138 1400 308 133
1325 314 134 1360 303 131

Figure 5-36. Cruise Performance (Sheet 2 of 13)

5-64 1 April 1998

For Training Purposes Only
 (

( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED
(
(
f CRUISE PERFORMANCE
\, PRESSURE ALTITUDE 4000 FEET
( COND IT[ ONS I
8000 POUNDS
INERTIRL SEPARRTOR - NORKRL
( REFER TO SHEET 1 FOR RPPROPRlRTE NOTES RPPLICABLE TO THIS CHRRT
TEHP 1900 RPH 1750 RP" 1600 RP"
( OEC [ TORDUE FUEL TORDUE FUEL TORDUE FUEL
n-us n.ow ~rRS F r -LBS FLOW HAS FT-LBS FLOW KTAS
( PPH PPH PPH
~O 1253 335 15~ 1340 335 lS~ 1431 335 152
1430 335 152
( 3D 1464 365 164 1562 365 163 1662 365 160
1300 339 155 1400 341 155 1500 341 154
( 1350 333 IS3 1415 330 150
20 1665 395 171 1712 395 170 1880 395 161,
1500 368 164 1600 3&8 1&3 1700 367 160
(
~~~~ . ~~~ ~~: ~~~~ ~~~ ~500
~~~ ~~~
154
151 405
to 1862 42& 117 1910 424 175 1970 405 168
( 1700 398 171 1800 396 169 1800 319 162
1500 366 162 1600 365 lSI 1600 349 155
( 1300
12B5
335 152 1400
1335
335
325
152 1400 32Z 146
332 151 149 1385 320 146
0 1865 425 175 1970 422 173 1970 401 161
( 1700 396 169 1800 393 167 1800 375 161
1500 363 160 1600 362 159 1600 346 153
/' 1300 332 150 1400 332 151 1400 145
( 318
( -10
1280
1865
329
423
149
173
1315
1970
320
419
146
171
1380
1970
315
397
144
165
( 1700 393 167 1800 390 165 1800 312 159
1500 361 158 1600 359 158 1600 343 152
( noo 330 149 1400 329 149 1400 315 143
171fi ~26 1~8 1305 315 144 1360 309 142
:20 1865 ~21 171 1910 ~16 169 1970 393 IS3
( 1700
1500
390
359
165
156
1900
1600
386
35&
1S3
IS6
IBOO
1600
369
339
151
150
1300 327 147 1400 326 147 1400 311 142
1265 3ZZ 145 1290 310 142 1345 304 i39
-3D 1865 419 169 1970 413 167 1970 390 161
1700 388 162 1800 383 161 1800 365 156
( J500 356 154 1600 353 154 1600 336 148
1300 325 145 1400 323 145 1400 J08 140
( 1265 320 143 1295 307 140 1340 300 138
-40 1865 411 166 1970 410 165 1970 387 159
1100 385 160 1800 380 159 1800 361 154
( 1500 354 152 1600 350 152 1600 332 141
143 1400 nD· 144 1400
i~~
1300 323 }38
1260 317 141 1280 303 138 1325 35
( -50 1865 415 164 1910 408 163 IHO ' 384 157
liDO 384 158 1900 377 157 1800 359 152
( 1500 351 150 1600 347 150 1600 329 145

~~~
1300 321 1400 317 142 1400 302 131
1760 115 1175 3DO 1]6 13ZD 291 133
-5~ 1865 414 163 1910 407 162 1970 383 156
1700 383 157 1900 377 156 1800 356 151
1500 350 1~9 1600 346 149 1600 328 144

~~~ ~!~ ~!~~ ;!~

141
;~~~ ~~~~ ;~1 }~~
(,,"> 35 89

Figure 5-36. Cruise Performance (Sheet 3 of 13)

1 April 1998 5-65

For Traininl! Purooses Only
SECTION 5 CESSNA (
PERFORMANCE MODEL 208 (675 SHP) J
(
CARGO POD INSTALLED

CRUISE PERFORHANCE
PRESSURE ALTITUDE BODO fEET
CONOrTIONS.
8000 POUNDS
INERTIAL SEPARATOR - NOR"AL
REFER TO SHEET 1 FOR RPPROPRIRTE NOTES RPPLICABLE TO THIS CHART
TE"P 190 RP" 750 RP" 1600 RPn
OEG C TORQUE FUEL TORQUE FUEL TORQUE fUEL
~~~U FT -Las· ~~~~
H-Las FlOU HRS rT -Las KTRS KTAS
PPH
35 1146 324 156 1331 324 155 1419 324 153
1305 320 154 1380 318 152
25 1444 353 166 1539 353 164 1635 353 162

~~~
1300 158 1400 332 158 1500 333 156
1250 155 _1300 316 152 1370 314 150
15 ISZ!! 381 172 173l 381 171 1835 381 168
1500 360 167 1600 360 165 1700 360 163
1300 3lS 156 1400 319 156 1500 330 154
1230 311 153 1290 312 150 1355 308 148
5 1814 413 178 1928 413 176 1970 400 ' 171
l700 390 173 1800 389 l1Z 1800 37Z 165
1500 357 IS5 1600 351 164 1600 341 157
1300 325 155 1400 326 155 1400 312 148
1230 314 151 1280 308 148 1345 305 146
-5 1865 421 178 1970 419 176 1970 397 169
1700 389 171 1800 381 170 1800 368 163
1500 355 163 IS00 354 162 1600 339 156
1300 323 153 1400 323 153 1400 309 141
1230 312 149 1275 304 147 1330 299 144
-15 1965 419 176 1910 416 174 1970 393 161
1100 387 170 1800 384 169 1800 364 ' 162
1500 353 161 1600 351 160 1600 335 15~
1300 321 151 1400 320 151 1400 306 145
H2O 308 147 1255 259 144 1310 293 141
-25 1865 417 174 1970 ~13 112 1970 389 165
1700 385 167 1800 381 166 1900 361 160
1500 350 159 1600 349 158 IS00 332 152
1300 319 149 1400 311 150 1400 303 144
1205 304 144 1135 2g3 lQl 1295 288 1]9
-35 1865 415 In 1970 411 170 1970 387 164
1700 383 165 1800 379 164 1800 358 158
1500 348 157 1600 345 156 1600 329 151
1300 316 148 1400 315 148 1400 300 142
1200 301 142 1230 290 139 1295 285 131
-<15 1865 413 169 1910 408 168 1970 384 162
1700 382 163 1800 316 162 1900 354 156
1500 345 155 1600 142 154 1600 325 149
1300 314 145 1400 312 146 1400 297 140
1205 300 140 1230 288 _138 1280 280 135
-54 1965 412 167 1970 405 ISS 1970 391 160
1700 380 161 1800 374 160 1800 352 154
1500 344 153 1600 340 152 1600 322 141
1300 313 144 1400 310 144 1400 294 139
1210 298 139 1225 284 136 12SS 275 133

Figure 5-36. Cruise Performance (Sheet 4 of 13)

5-66 1 April 1998

For Training Purposes Only
 (

( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED
(
(
CRUISE PERFORHANCE
PRESSURE RLTITUDE 8000 FEET
( CONOITI01IS.
8000 POUNDS
(
INERTIAL SEPARATOR ~ NOR"AL
REFER TO SHEET 1 FOR APPROPRIRTE NOTES RPPLICRBLE TO THIS CHART
( TEMP .qon RPM 1750 RPIt 1600 RPH
OEG C TOROUE FUEL TOROUE FUEL TORQUE FUEL
rT-LBS nDW KrRS FT -LBS FLDW KrRS
( PPH
FT -LBS
~~OW KTAS
PP" PH
30 lZ14 311 157 lZ96 311 156 1381 311 154
1260 305 15~ 1335 304 151
2D 1395 339 166 1495 339 164 1577 338 162
1205 307 155 1300 309 155 1400 311 153
( 1250 301 152 1325 299 1119
10 1569 364 In 1667 3G~ 171 1765 364 IG8
1400 336 164 1500 337 16~ 1600 338 161
( 1200 304 153 1300 306 153 1400 308 152
1190 302 153 1250 298 51 1310 295 I'll
( 0 1140 396 178 1849 396 176 1954 396 1"73
1600 368 17Z 1100 358 171 1800 367 168
1400 334 163 1500 334 162 1600 334 160
( lZ00 302 151 1300 303 152 1400 305 151
1175 Z98 150· 1235 294 148 1290 299 IllS
( -10 1865 419 181 1970 411 179 1910 396 172
1700 386 175 1800 385 173 1900 364 166
1500 348 166 1600 34B 165 1600 331 158
( 1300 316 156
14~~ 3~: 156 1400 302 1119
1175 296 149 121 Z8 146 1210 284 1113
-20 1865 417 179 1970 414 177 1970 392 1"70
( 1700 395 172 1800 392 171 1800 360 164
1500 346 164 1600 345 163 HOD 328 156
( ~~~~ ;~~ ~~~~ ;~~
154 154 1400 233 148
147 144 1260 279 14'
-3~ 1865 415 177 1970 411 175 1970 388 168
( 1700 383 170 1800 380 169 lBoO 358 162
1500 344 162 1600 342 161 1600 325 155
1300 311 152 1400 310 152 1400 296 146
( 1170 290 145 1200 Z81 141 U50 275 139
-40 1865 413 174 1970 409 172 1970 395 166
( 1700 391 169 1800 377 167 1900 35.5 160
1500 342 160 1600 340 159 1600 322 153
1300 309 150 1400 308 150 HOD 293 144
( 1160 287 142 ~200 279 140 1Z45 271 137
115 275 139
( -50 1865 410 172 1970 41lS 170 1970 382 164
1700 379 166 IBoD 3N 164 1900 352 159
1500 341 157 1600 338 157 1600 319 151
( 1300 307 149 1400 3115 148 HOD 290 143
1160 286 140 1200 276 138 1235 266 135
11An 27~ 137
( -54 1865 410 171 1910 4114 169 1970 381 163
1700 378 165 1800 373 164 1800 352 159
( 1500 341 157 1600 337 156 1600 318 150
1300 306 147 1400 304 147 1400 299 I'll
1165 Z86 140 1200 ~75 137 1225 264 134
( 1180 7Z 1'6

Figure 5-36. Cruise Performance (Sheet 5 of 13)

1 April 1998 5-67

For Traininl! Purooses Onlv
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

CARGO POD INSTALLED

CRUISE PERFORHANCE
PRESSURE ALTITUDE 10000 FEET
CONDITIONS.
8000 POUNDS
INERTIAL SEPARATOR - NORKRL
REFER TO SHEET 1 FOR RPPROPRIRTE MOTES RPPLICRBLE TO THIS CHRRT
1E~P 1900 RPn 175D RPn ,00 RP~

OEG C TOROuE FUEL TOROUE FUEL TORQUE FUEL

fT -LOS FLOW KTAS f1-Las FLOII KTAS FT -LOS FLOW KTAS
PPH PPH PPH
25 1181 298 157 1260 298 156 1341 298 153
1115 291 157 lZ15 291 153 1290 290 150
15 1343 322 166 1430 322 164 1517 322 161
1200 299 157 1300 302 157 1400 304 155
1170 294 155 1205 281 152 1290 201 149
5 1506 349 173 1601 349 171 1694 349 168
1400 329 167 1400 315 161 1500 316 159
1200 291 155 1210 285 150 1300 291 149
1155 290 153 1280 283 148
-5 1663 319 178 1167 ,379 176 1865 319 173
1500 3~6 171 1600 3~1 16~ 1100 341 166
1300 311 160 1400 312 159 1500 313 158
1150 286 151 1200 281 148 1300 204 141
1255 211 145
- 15 1806 405 182 1919 405 180 1910 395 175
1700 384 118 1800 383 175 1800 363 169
1500 345 169 1600 345 167 1600 326 160
1300 309 158 1400 310 158 1400 296 151
1145 283 149 1200 219 141 1240 272 143
J190 211 146
-25 1865 415 182 1910 412 180 197G 391 173
1100 382 \15 1800 380 17~ 180G 359 161
1500 3~3 lin 1600 342 165 limo 323 159
1300 307 156 1400 306 156 1400 293 150
1135 Z80 141 1200 Z16 145 1215 266 140
1115 212 1~~
-35 1865 412 180 1910 410 177 191G 388 111
1100 380 173 180G 378 111 18GG 356 165
1500 342 165 1600 340 163 1600 3Z0 157
1300 30~ 154 '1'100 304 15~ 1400 290 148
1135 218 145 1200 214 144 UOO 261 138
1160 268 141
-~5 1865 411 111 191G 401 175 1910 38~ 169
1100 318 171 1800 315 169 1800 353 163
1500 3~0 162 1600 337 161 160G 318 155
1300 302 152 140G 301 153 1400 287 147
1130 216 143 1200 212 1~2 1200 258 136
1150 264 139
-5~ 1865 410 175 1910 405 113 197G 380 161
1700 377 169 IBOG 31. 161 laOG 351 161
1500 339 160 1600 336 160 1600 316 154
1300 301 151 1'100 299 151 1'100 284 145
1125 213 141 1200 210 140 1200 256 135
1145 261 137 1190 254 134

Figure 5-36. Cruise Performance (Sheet 6 of 13)

5-68 1 April 1998

ForTraining Purposes Only
 (

( CESSNA SECTION 5
MODEL 20B.(675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED
(
CRUISE PERFORHRNCE
( PRESSURE ALTITUDE 12000 FEET
( CONDITIOIIS.
8000 POUNDS
INERTIRL S£PRRRT1IR - NDR"RL
( REFER TO SHEET 1 FOR RPPRoPRIATE NOTES RPPLlCRBLE TO THIS CHART
TEKP fg[jji RPK 750 RPK 1I;0~ RPK
( OEG C TOR DUE FUEL lORQUE FUEL TORQUE FUEl
rr - LBS FlOII KTRS rr -lBS FLolI KTRS FT-LBS FLOII KTRS
PPH PPH PPH
( 20 1137 284 157 1213 284
!~~~
155 284
170n '87 154 781 }~~
( 10 1285 306 165 1368 306 163 1450 306 160
1155 285 157 1195 279 153 1300 283 152
1275 279 ISO
( 0 1435 333 112 1525 333 170 1614 333 161
1300 301 164 t400 310 164 1500 311 162

!~~~ ~?7
1145 154
~~~ ~:~~
281 280 151
( 75 273 148
-10 1583 361 177 1681 361 175 1776 361 172
( 1400 325 188 1500 326 167 1600 327 165
1200
i~~
1300
~;~
289 157 1400 293
IB5 Z7A U8!; i5n 174n 769 ~~~
( -20 1106 384 181 1812 384 179 1912 383 176
1600 363 176 liDO 363 174 1800 362 111
( 1400 323 166 1500 324 165 1600 324 163
1200 281 155 1300 288 155 1400 290 153
( - 1125 274 150 1165 267 147 1725 264 14<1
( ,
l·
-30 1828 408 184 IS41
1800
408
379
181 IS70 391 176
1100 380 119 176 1800 359 169
"- 1500 341 170 1600 341 168 1600 3Z1 161
( 1300 302 159 1400 303 159 1400 297 152
~;~~ ~~~ ~:~
1115 271 148 1205 258 141
( -40 1865 415 183 1970 41Z lBO 1970 3BB 17<1
1100 379 176 1800 376 174 1800 355 161
( 1500 339 167 1600 339 166 1600 319 159
1300 300 157 1~00 300 157 1~00 28~ 150
1105 261 145 1200 26B 14. 1195 25~ 139
( IlSO 260 143
-50 1865 413 180 1910 410 178 1910 385 112
( 1700 377 174 1800 374 172 1800 352 IGS
1500 33B 165 1600 336 164 1600 317 158
1300 299 155 1~00 299 155 1400 28Z 1~9
(
!~~g ~52
1110 266 1~4 266 144 lZOO 138
255 I ~O 1180 49 137
-54 1865 412 IBD 1970 409 177 1970 383 171
( 1700 376 173 1800 373 171 1800 351 165
1500 331 16Q 16DO 335 163 1600 316 157
( UOO 299 154 1400 298 154 1400 280 148
1105 264 143 !200 265 143 1200 251 137
125 253 139 1175 247 136
(
(
(
(
(
.
~ ~..
';'~~-j

Figure 5-36. Cruise Performance (Sheet 7 of 13)

1 April 199B 5-69

For Trllininp Purnoses Onlv
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

CARGO POD INSTALLED

CRUISE PERFORMRNCE
PRESSURE RLTITUDE 14000 FEET
CONDlnONS.
8000 POUNDS
INERTlRl SEPRRRTOR - MORltRl
REFER TD SHEET 1 FOR RPPROPRIATE NOTES IIPPLICIIBLE TO THIS CHIIRT
TEHP 1900 AP" 1750 RP~ 1600 RPH
OEG C roROUE FUEL IORQUE FUEL 10ROUE FUEL
FLOW KTRS FT-LBS
~~~N
FT -L9S KIRS FI-lBS FLOW KIRS
PPH PPH
15 087 no L55 1159 270 153 1232 270 50
5 1226 291 164 1304 291 IS2 1383 290 159
1150 278 159 1185 271 154 1260 271 151
-5 1363 317 171 1449 317 169 1533 317 166

~:: ~~~~ !~~

1200 284 161 1300 ISO 291
. 1135 273 l56 l' 7[) 152 2&7
-15 1495 342 176 1589 342 174 1678 342 171
1300 303 165 1400 '.
305 ISS 1500 308 162
1120 269 154 1200 269 153 1300 272 151
1165 263 150 1235 262 141
-25 1606 362 180 1101 362 117 1801 362 174
1500 341 174 1600 342 113 1600 324 165
1300 301 164 1400 303 IS3 1400 296 155
1115 266 151 1200 266 151 1215 257 145
1160 260 49
-35 1721 386 182 1827 386 180 1927 386 111
1600 359 177 1100 359 175 1800 359 17Z
1400 319 167 1500 320 16& 1600 320 164
1200 280 156 1300 282 156 1400 284 154
1100 262 149 1150 251 141 1200 253 142
1190 251 142
-45 1844 410 185 1957 410 193 1970 392 111
1700 380 119 1800 319 177 1800 356 110
1500 337 110 1600 337 169 1600 318 162
1300 298 160 1400 299 159 1400 282 152
1100 260 141 1200 263 148 1200 250 141
1080 251 146 1135 252 1'14 1180 246 140
-54 1865 412 184 1970 410 181 1970 388 175
1100 379 171 1800 316 115 1800 353 168
1500 33G 1GB 1600 335 161 IGOO 31S ISO
1300 297 158 1400 297 158 1400 Z80 151
1100 259 145 !ZOO 2£0 14£ 1200 247 140
1080 256 U4 1120 248 ' 141 1170 243 138

Figure 5-36. Cruise Performance (Sheet 8 of 13)

5-70 1 April 1998

For Training Purposes Only
CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE

CARGO POD INSTALLED

CRUISE PERFORHANCE
PRESSURE ALTITUDE 16000 FEET
CONDITIONS.
aooo POUNDS
INERTIRL SEPRRRTOR - NDRKAL
REFER TO SHEET 1 FOR RPPROPRIRTE NOTES RPPLICABLE TO THIS CHRRT
TEMf LSOO RP" 150 RP" bon RPM
OEG C TORQUE FUEL lORQUE FUEL TORQUE FUEL
FT-LBS FLOW HRS FT-LBS FLOW KTRS Fl-LBS FLOW KTRS
PPH PPH PPH
10 1040 256 1~3 1 09 256 151 1111 256 141
0 1168 277 162 1243 211 160 1311 Z71 151
1125 26S 159 1195 266 156 1260 267 153
-10 1292 301 169 1373 301 167 1'452 300 164
1110 265 157 1200 261 156 1300 Z71 154
1165 260 153 1245 261 151
-20 140. 322 174 1493 322 172 1517 3Z2 169
1300 301 168 1300 284 161 1400 ZBB 159
1110 263 155 11.0 257 152 1235 257 149
-30 150B 342 178 1602 341 175 1691 341 112
1400 319 In 1400 302 165 1500 304 163
1200 219 160 1200 263 153 1300 266 15Z
1085 256 152 1145 253 150 1210 251 146
-40 1611 365 1Bl 1715 364 179 1810 364 115
1500 33B 175 ·1600 339 174 1700 340 111
1300 298 164 1400 300 164 1500. 301 llil
1100 259 151 1200 262 152 1300 265 151
1010 25Z \49 1125 248 147 1190 246 144
- 50 1130 386 184 IUS 386 181 1935 385 179
1600 359 179 1100 359 176 1800 359 113
1400 316 169 . 1500 317 167 1600 317 164
1200 277 156 1300 219 156 1400 281 1511
1045 241 145 1115 244 145 1200 245 143
1180 241 142
- 54 1729 395 183 1934 384 180 1934 383 171
1600 358 177 1700 358 115 1900 357 172
1400 315 167 1500 316 166 1600 316 163
1200 271 155 1300 Z1B 156 1400 290 154
1035 244 144 1110 . 242 143 1200 244 142
1160 237 140

Figure 5-36. Cruise Performance (Sheet 9 of 13)

1 April 1998 5-71

For Training Purposes Only
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

CARGO POD INSTALLED

(
CRUISE PERFORHANCE (
PRESSURE ALTITUDE 18000 FEET
CONDITIONS.
8000 POUNDS
INERTIftL SEPRRATOR - NOR"Rl
REFER TO SHEET 1 FOR APPROPRIfiTE NOTES APPLICABLE TO THIS CHRRT
TE"P 1900 RPM 1750 RPM 1600 RPM
DEC [ TDRDUE FUEL lDRDUE FUEL TORIlUE FUEL
rt-LBS FLOW KfAS FT -LBS FLOW KTAS FT -LBS FLON KTAS
PPH PPH PPH
5 993 2q3 150 1058 243 147 1 23 741 43
-5 1109 2&3 160 1119 263 157 1250 263 154
1075 256 157 1140 255 154 1225 258 151
-15 1223 285 167 1299 295 165 1374 285 161
1100 260 158 1120 250 152 1205 252 149
1060 252 154
-25 1319 303 172 1401 303 1&9 1481 303 16&
1200 27S 164 1200 264 157 1300 2&9 155
1060 251 153 1105 245 150 11'10 247 141
-35 1412 321 176 1500 321 173 1584 321 170
1300 298 169 1300 281 162 1400 284 160
1100 258 155 1095 241 147 1200 247 147
1035 245 150 1170 242 145
-45 1511 342 179 1603 342 176 1694 342 113
1400 318 173 1400 299 1&6 1500 301 164
;;~
1200 276 161 1200 2GO 154 1300 153
1015 240 146 1015 23& 145 1150 142
-54 1560 350 179 1653 350 177 1745 349 l1q
1400 316 171 1500 318 170 1600 319 161
1200 275 159 1300 211 159 1400 280 151
(
~~g~
995 235 143 1100 240 145 244 145
1010 234 lq3 231 140
(

(
(

(
(

(
(

Figure 5-36. Cruise Performance (Sheet 10 of 13)

5-72 1'April 1998

For Training Purposes Only
{ CESSNA SECTION 5
( MODEL 208 (675 SHP) PERFORMANCE

(
CARGO POD INSTALLED

( CRUISE PERFORHANCE
PRESSURE ALTITUDE 20000 FEET
( COIIO IT lOllS I
7500 PDUIIDS
( [NEIITIRL SEPRIIRTDII - ~ORIML
REFEII TO SHEET 1 FOR APPROPRIRTE NOTES RPPLlCRBLE TO THIS CHRRT
( TEKP 1900 RPK 1750 R?K 1600 RP"
DEG C TOROUE FUEL TOROUE FUEL TORQUE FUEL
FT -lBS FLOW HRS FT -lBS FLOW KTAS FT -l9S flOW KTRS
( PPH PPH PPH
0 9~2 229 lSI 1003 . 229 1~8 10S~ 229 1~4
( -10 10~1 2~9 160 1I1~ 2~9 158 1180 2~9 154
990 238 155 1050 236 153 1130 239 150
- 20 1150 268 167 1222 26B 165 1293 269 161
( 100S 239 155 1100 2~5 156 1110 233 148
1035 231 150
{ -30 1136 IB4 172 1312 184 169 1388 284 166
1100 257 162 1200 262 162 1200 24B 154
990 235 153 1020 227 148 1100 229 145
( -40 1322 301 175 1~0~ 102 173 I~B3 302 170
1200 276 167 1100 261 161 1300 265 159
1000 236 152 1010 224 146 1100 227 145
( 9~5 225 1~7 1075 223 1~3
-50 1414 321 178 1499 320 176 1582 320 173
( 1300 296 112 1300 Z7B 165 1400 281 163
1100 255 ISS 1100 239 152 1200 24~ 151
935 222 1~5 990 21B 143 1060 21B 140
( -54 140B 319 171 149~ liB 175 1579 31B 172
1300 296 171 1300 211 164 1~00 280 162
( 1100 254 158 1100 239 151 1200 243 150
925 220 143 1000 220 143 1050 216 140

{
(
(

Figure 5-36. Cruise Performance (Sheet 11 of 13)

1 April 1998 5-73

SECTION 5 CESSNA (
PERFORMANCE MODEL 208 (675 SHP) (

(
CARGO POD INSTALLED

CRUISE PERFORMANCE (
PRESSURE RLTJTUDE 22000 FEET
CONonIOIIS. (
'1000 POUNDS
INERTIRL SEPARRTOR - NOR"RL
REFER TO SHEET 1 FOR RPPROPRIATE NOTES RPPLlCRBLE TO THIS CHRRT
TE"P 1900 RP"_ 1751) RPn 1600 RP"
OEG C TOR DUE FUEl TOROUE FUEL TORQUE FUEL
rT -LBS HOH KrRS Fr-lBS HOH KTRS Fr-lBS fLOH KrRS
PPH PPH PPH
(
-5 . BBB 16 152 94:; 15 49 1003 Z15 4:;
-15 9B4 234
. 222
161 1046 234 15B 1109 234 155 (
925 155 975 219 152 1045 221 149
-25 1073 251 167 1141 251 IS.5 1208 251 161
925 221 154 1000 223 153 1100 230 . 153 (
950 214 149 1035 211 141
-35 1153 266 111 IllS 266 169 1296 266 166 (
1000 235 159 1100 241 160 1100 227 152
910 211 151 9AO 210 147 1010 211 144
-4S 1234 283 175 1311 283 173 1387 283 169 (
1100 254 166 1200 259 166 12DO 244 158
900 214 147 1000 220 151 1000 20B 142
860 206 144 925 206 144 9SO 20S 141 (
-54 1269 290 115 1347 289 173 142S 289 170
1100 253 164 1200 258 164 1300 262 163 (
900 213 141 1000 219 149 1100 224 149
B70 207 144 915 203 142 970 201 139
(
(
(
(
(
(
(
(
(
(
(
(
(
(
Figure 5-36. Cruise Performance (Sheet 12 of 13) (

5-74 1 April 1998

For T raining Purposes Only
 ( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED
(
CRUISE PERFORHANCE
( PRESSURE ALTITUDE 24000 FEET
( CONDITIONS.
6600 POUNDS
INEATIAL SEPAAATOR - NORMAL
( REFER· TO SHEET 1 FOR RPPROPRIATE NOTES APPLICRBLE TO THIS CHRRT
TEMP 1900 RPM 1750 RPM 1600 RPH
( OEG C TORQUE FUEL TORQUE FUE~ TOROUE FUEL
Fl-LBS FLOW KIRS F)-LBS FLOII KIRS FT -LBS FLOW KTRS
PPH PPH PPH
( -10 936 203 153 990 2 3 151 945 203 146
-20 925 220 162- 994 ZZO 159 1043 2Z0 156
{ 855 Z06 154 890 lOl 150 970 205 148
-30 IDOl 235 167 1066 l35 165 1129 l34 161
860 205 153 900 202 150 1000 209 151
( 880 198 148 950 ZOO 146
-40 1076 249 171 1143 249 169 1210 249 166
( 900 213 156 1000 220 159 1100 227 158
915 196 141 810 195 146 930 195 143
-50 1151 265 175 1222 265 17Z 1Z92 264 169
( 1000 Z3Z 163 1100 Z38 164 1100 ZZ4 156
805 193 144 900 199 148 910 190 140
( 850 190 143
-54 1144 263 173 1216 263 171 1Za8 263 168
1000 232 163 1100 238 164 1100 2Z4 156
( 905 192 144 900 199 141 900 187 139
810 ill 144
( ('
t
( ~
(
(
(
(
(
(
(
(

(
(

Figure 5-36. Cruise Performance (Sheet 13 of 13)

1 April 1998 5-75

For Training PUrposes Only
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP) (

CARGO POD INSTALLED

FUEL AND TIME REQUIRED
MAXIMUM CRUISE POWER (40 • 200 Nautical Miles)
(
CONDITIONS :
BOOO Pounds 1900 RPM Inertial Separator - Normal Standard Temperature (
NOTES :

1.) Fuel required includes the tuel used tor engine slart, ta xi, takeoH, maximum climb trom sea tevel, descen t 10 sea
tevel and 45 minutes reserve. Time required includes the time during a maximum climb and descent.
2.) With inertial separator in BYPASS or cabin heat on, increase lime by 3% and tuel by 2%.

12 00

1000 ~\..

V-
~
'O<c,~6.000

~
./' ~
'G~oQ
(
... f:- - 1- - .I- i- i- ----
~
(
d 600
V-
::J
"- I-'" V (
Y 1--:1-'
41110
-- 140

,
(
20 (
200
,
00 ~ (

oqf't
~ ... ~

~ .. ao ~
60 W

~
(
~r
\-IO\J~ 40
(
I<!if$i e.V
~Il''''' 20 (
60 '" /' V- (
/'
/'
v:
V
V
V (
bl I", V
~i ifl ... rI ...
(
60

OI ST~NCE . N... UTlC ... L MILE S

Figure 5-37. Fuel and Time Required - Maximum Cruise Power

40 - 200 Nautical Miles (Sheet 1 of 2)

5-76 1 April 1998

For Train ing Purposes Only
( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED
(
FUEL AND TIME REQUIRED
MAXIMUM CRUISE POWER (200 ·1000 Nautical Miles)
( CONDITIONS:
8000 Pounds 1900 RPM Inertial Separator - Normal Standard Temperature
NOTES:

1.) Fuel required includes Ihe fuel used for engine slarl, laxi, lakeoff, maximum climb from sea level, descenlto sea
( level and 45 minutes reserve. Time required includes Ihe time during a maximum climb and descent.
2.) With inertial separator in BYPASS or cabin heat on, iQcrease time by 3% and fuel by 2%.

( 2400
1- --
(

( ZIlIlI!!

V
( ·f--I- r<i;'1 V
tn lOll!!! I$(
'''': ~~/
~ c
~t)~
( ",'JJ'
(
17
( 1 IY 7
k' ~)", l-
( '1-(;) 6
I
-
( 41211!! :I ~
7"~~(;) ::>
o
SEA LEVEL 4 J:
( t'&
W
I/.:
~/.~
3 ~
( k;:::

17
~ ... -1- - 1-- -1-1-
2

( 69
--
I!? ~40 1/
0'"
z c II V
'" <
, ~20
II .I 1/
V V 1/ IL
r-t- I~ / II 1/ V
I II 1.1 V
I ... "'I ~/I "
/'OJ '0 I~

60 / V

DISTANCE - NAUTICAL MILES

Figure 5-37. Fuel and Time Required - Maximum Cruise Power

200 - 1000 Nautical Miles (Sheet 2 of 2)

1 April 1998 5·77

For Trllininll Purnoses Onlv
 (
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP)

CARGO POD INSTALLED

FUEL AND TIME REQUIRED
MAXIMUM RANGE POWER (40 - 200 Nautical Miles)
CONDITIONS:
8000 Pounds 1900 RPM Inertial Separator· Normal Standard Temperature
NOTES: (

1.) Fuel required includes the luel used lor engine start, taxi, takeoff, maximum climb from sea level, descent to sea
level and 45 minutes reserve. Time required includes the time during a maximum climb and descent.
(
2.) With inertial separator in BYPASS or cabin heat on, increase lime by 3% and fuel by 2%.
(
(

18111111

~f?"
~fl110 "'~
AIJ;;
(
IIIQlI'
V :.-J (
I-'"" k ,6.r§IJ
;:;j61l0
I-'"" "=I;:::P'"
...
=>
... V
P
"",P' ~ZOOO

(
all0 140

1.1 120 (
20121
! ,00 "'w (
!:i
2
80 ~
\.."1\"1~
O~S (
- 60 w
"'~ 1- 40
::!!
;:: (
1.0>'
.... 20 (

15e (
1/
-- P
1/ (

V V
!- ,. ·!-I:t;· t-.
I'!I 1/

...
--
611 (
DISTANCE· NAUTICAL MILES
(

Figure 5-38. Fuel and Time Required - Max Range

40 - 200 Nautical Miles (Sheet 1 of 2) (

5-78 1 April 1998

For Training Purposes Only
( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(

( CARGO POD INSTALLED

FUEL AND TIME REQUIRED
MAXIMUM RANGE POWER (200 -1000 Nautical Miles)
( (~
CONDITIONS:
( 8000 Pounds 1900 RPM Inertial Separator - Normal Standard Temperature
NOTES:
(
1.) Fuel required Includes the luel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea
( level and 45 minutes resorve. Time required includes \he lime during a maximum climb and doscent.
2.) Wilh inertial separalor in BYPASS or cabin heal on. increase lime by 3% and luel by 2%.
( ZUII'"

(
( ~ .

~~-Sj..I-1-~ IL 0/ /
1
( ~'t, \f'~ ~~
~r- J()'
V
:;- ~r-'1
( /'
~I2"'11J
IL I
( /'

( ( B00
V
b
7
~... ~ "

\~~ ()
( ~ 'l-()' 6
IV
IT L.
400 5g?
(

( I~ \:}<J
~
i{c;,
'" :;)
o
4:1:
w
"1.\"1. 3;;
VI''' f-
( 1'"" I,
2

( I'
I'

V 1/ I ......

:/ V t.--
1..>0 1/ V
II V 1/
II 1/
V 1./ 1/
I I 1/ 17 V 1/

I"" ~/I~ V..il

1;/ 10, It! IW
'" V
II If V /

DISTANCE - NAUTl~AI.. HII..ES

Figure 5-38. Fuel and Time Required - Max Range

200 - 1000 Nautical Miles (Sheet 2 of 2)

1 April 1998 5-79

For Trainin~ Purooses Onlv
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP) (

(
CARGO POD INSTALLED
(
RANGE PROFlLE
45 MINUTES RESERVE
2224 LBS USABLE FUEL (

CONDITIONS: NOTES: (
1. 'This chart allows for the fuel used for engine start,
8000 Pounds taxi, takeoff, climb and descent. The distance
1900 RPM during a'maximum climb and the distance during
Standard Temp descent are included.
Zero Wind
Inertial Separator. Normal 2. With the inertial separator in BYPASS or cabin heat
on, decrease range by 2% .
(

25000
111111 (
IIII III
IIII II r
15M~~S (
'65 KTA
153 KTAS
(
21i!000

I- 173 KTAS
W 150 KTAS (
W !t)
I.J.. 1::1000 if { .(
<l
tv
W
0
,,::,-Si I
177 TA
::J
l-
<TIll 150 KTAS
I-
..J
<:
10000
~~
~ .r'"
~# ~
(

(
I}(
11~81~~~S
5000
mmll }J rl151 KTAS

mmll #1 II
~ (
r~OI~)~~ ;.liy
IA'I
I
WI~lj'iSI
" (
" """
1111 I
N..YI (..!1" 1111111
SL
flllil 701i! BIlIi! 900 1e0e 1 11i!0 1200 1300 1400 1500 1B00
RANGE - NAUTICAL MILES

(
(

. Figure 5-39. Range Profile

5-80 1 April 1998

For Training Purposes Only

 ( CESSNA SECTION 5
MODEL 208 (675 SHP) PERFORMANCE
(
( CARGO POD INSTALLED

ENDURANCE PROFILE
45 MINUTES RESERVE
2224 LBS USABLE FUEL
CONDITIONS : NOTES:

1. This chart allows for the fuel used for engine start,
8000 Pounds tax i, takeoff, climb and descent. The distance
1900 RPM during a maximum climb and the distance during
( Standard Temp descent are included .
Inertial Separator - Normal
( 2. With the inertial separator in BYPASS or cabin heat
on, decrease endurance by 2 %.
(
( 25000

(
(
20000
(
I-
( f" W
W

(
t --~
l1..
15IIl11l11l
W
0
( :::l
l-

( I-
..J 1011100
<
~~~~~~~~~~~O~~'H4~H+~H+~H++1
(
(v'I. H-t+Hl++tH++-H+~H-H
~~~~~4+~~~~'~G'++~~~++~~~~
~.++~++~~H++H+¥~~-++H4++~~~+H~+h~
500111 ~+M~H4~~~~~~'~~~++~++~+H~++~
ww++~++~+H~~~~rl4++~~~~~~~~~
/

~~~H4~~~~~~-~~~~4+H4~H4~~++H
iii
II
SLLU~WU~U4~~~~III~LU~LU~~~~~~~WU
4.0 5. 0 6.0 7.0 6.0 9.0
ENDURANCE HOURS

Figure 5-40. Endurance Profile.

1 April 1998 5-81

For Trainine Purposes Only
SECTION 5 CESSNA
PERFORMANCE MODEL 208 (675 SHP) (

(
CARGO POD INSTALLED
(

(
TIME, FUEL AND DISTANCE TO DESCEND
(
(
CONDITIONS :
(
Flaps Up (
8000 Pounds
140 KIAS Above 16,000 feet, (
160 KIAS Below 16,000 feet (
Power Set for 800 FPM Rate of Descent
1900 RPM (
(

DESCEND TO SEA LEVEL (

PRESSURE
ALTITUDE TIME FUEL USED DIST
(FEET) (MIN) (POUNDS) (NM)
(
(
24,000 30 132 91
20,000 25 113 . 75 (
16,000 20 95 59 (
12,000 15 72 43 (
8,000 10 48 .28
4,000 5 25 14
Sea Level 0 0 0

(
NOTE
(
Distances shown are based on zero wind.
i" (
(
Figure 5-41. Time, Fuel and Distance to Descend

5-82 1 April 1998

For Training Purposes Only
 ,r, "·",\
~ ,;

» S':o
"0 LANDING DISTANCE Om
~. oen
-'- MAXIMUM WEIGHT 7800 LBS
men
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(0
(0 SHQRT FIELD 1\)>
en CONDITIONS: . NOTES: 0
1. Short~fi~le~ld~tec~hn~i~qu~e~a~s~sp~e~c~ffi~ed~in~Soc~ti~0-n~4-.----~-------------------------- en
"
cO·
...,
t:
Aaps 30·
Power lever - Idle after clearing
obstacles, BET A range (lever
2 . Decrease distances 10% for each 11 knots headwind. For operation with tailwinds up to 10
knots. increase distances by 10% for each 2 .5 knots.
m
.......
(l)
against spring) after 3. For operation on a dry. grass runway. increase distances by 40% of the "ground roll" figure. 01
(1l touchdown. 4. If a landing with flaps up is necessary, increase the approach speed by ·'5 KIAS and allow en
.J:,. Propeller Control lever - MAX for 40% longer distances. . J:
!'> Maximum Braking 5. Use of maximum reverse thrust after touchdown reduces ground roll by approximately 10%. ~
Paved, level, Dry Runway 6 . Where distance values have been replaced by dashes. operating temperature limits of the 0
;' r Zero Wind airplane would be greatly exceeded. Those distances which are included but the operation >
"I
III Cargo Pod Installed slightly exceeds the temperature limit are provided for Interpclation purposes only. :u
-i ::::J C)
"I 0. 0
:II 5· SP~£D ~ 1O'C O'C 1O'C 20'C 30'C 4O'C
:i- to WEIGHT AT PRESS
GRD TOTAL FT GRO TOTAlFT GRO TOTAL FT GRO TOTAL FT GRO TOTAL FT GRD TOTAL FT ."
S- LBS 50 FT AU
ROLL TO CLEAR ROll TO CLEAR ROll TO CLEAR ROLL TO CLEAR ROlL TO CLEAR ROll TO CLEAR
0
Q 0 FT 0
en· KIAS FT 50 FTOBS FT 50 FT08S FT 50 FTOBS FT 50 FT OBS FT 50 FTOBS FT 50 FTOBS
~ ill 7800 78 S.l. 650 1500 675 1540 700 1580 720 1620 745 1660 770 1700
Z
en
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::::J
~
1000 670 1540 700 · 1580 725 1620 750 1660 775 1705 800 1745
= 0
(l) 2000 695 1580 725 1620 750 1665 775 1705 805 1750 830 1790
r-
"
!II 3000 725 1620 750 1665 780 1710 805 1750 835 1795 860 1835
r-
"
:l en
:T
4000
5000
750
780
1665
J710
780
810
1710
1755
810
840
1755
1805
835
870
1800
1850
865
900
1845
1895
895
925
1885
1940
m
0
:s (l) 6000 810 1755 840 1805 870 1850 900 1900 930 1945 965 1995
~ ~ 7000 · 840 1805 870 1855 905 1905 935 1955 970 2000 1000 2050
8000 875 1855 905 1905 940 1955 975 2010 1005 2060 1040 21 0 5

2-
9000
10.000
905
945
1910
1965
940
980
1960
2015
975
1015
20 15
2070
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1050
2065
2125
1045
1085
2115
2180
-
- _.
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11.000 980 2020 1020 2075 1055 2130 1090 2185 1130 2240 - -- m
~ 12.000 1020 20BO 1060 2135 --l OSS 2195 1135 2250 1175 2310 - - :D
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7300 LBS AND 6800 LBS 0-
SHORT FIELD :DO
REFER TO SHEET 1 FOR APPROPRIATE CONDITIONS AND NOTES s::Z
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t:
SPEED
AT
PRESS
- 1O"C O'C 10'C 20'C 3O'C 4O'C Z
()
.... WEIGHT
AlT GAD TOTAL FT GAD TOTALFT GAO TOTAL FT GAO. TOTAL FT GRD TOTAL FT GRD TOTAL FT
m
co lBS SOFT
FT ROLL TO CLEAR ROll TO ClEAR ROll TO CLEAR ROll TO CLEAR ROll TO ClEAR ROll
~
U1 KIAS FT 50 FTOBS FT 50 FTOBS FT 50 FT OBS FT SO FTOBS FT SO FT OBS FT
TO CLEAR
50 FT OBS
.,
Q ~ 7300 75 S.L. 610 1430 630 1465 655 1505 675 1540 700 1580 725
I\) 1615
1000 630 1-465 655 1505 680 1545 700 1580 725 1620 750 1655
.,-l r-
2000
3000
655 1505 680 1545 705 1585 730 1625 I 755 '1660 780 1700
0
~
I>l 680 1545 705 15B5 730 1625 755 1665 780 1705 805 1745
S· Q)
4000 705 1585 730 1625 755 1670
:lJ
:J 785 1710 810 1755 835 1795 G>
E:i" 0. 5000 730 1625 760 1670 785 1715 815 1755 B40 1800 870 1845 0
IJCI S· 6000 760 1670 785 1715 815 1760 845 1805 875 1850 900 1895
<0 7000 785 1715 815 1765 845 1810 875 1855 905 1900 "1:1
~ 935 1945
.,= 0
8000
gOOD
820 1765 850 1815 880 1860 910 1910 940 1955 975
_. 2000 0
_.-.
8[;0 181!; 880 186[; 915 1915 945 1960 980 2010 0
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11 ,000
885
920
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1920
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1915
1970
950
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1970
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2020
2075
1020
1060
2070
2130
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12,000 955 1975 990 2030 1030 2085 1065 2140 1100 2190 -. _. -4
0 co 6800 72 S.L. 565 1360 585 1400 610 1435 630 1470
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650 1505 670 1540 r
:I 1000 585 1395
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610 1435 630 1470 650 1505 675 1545 695 1580 r
2000 605 1435 630 1470 655 1510 675 1545 700 1585 725 1620 m
'::J 3000 630 1470 655 1510 0
680 1550 700
s::
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1585 725 1625 750
co 4000 655 1510 680 1550 705 1590 730 1630 755
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6000
7000
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705
730
760
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790
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760
785
820
1630 ,
1675
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755
785
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1720
1765
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780
810
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875
1715
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850
885
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1870
880
915
1865
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1970 _.- -
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CO
11,000 855 1825 885 1875 920 1925 950 1975 985 2025 -
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