TABLE OF CONTENTS

SECTION 5

PERFORMANCE

Paragraph Page
No. No.

5.1 General .................................:........

5-1
5.3 Introduction Performance -

and Flight Planning ....... 5-!

5.5 Flight Planning Example
...................'........

5-3
5.7 Performance Graphs ............................... 5-9
List of Figures ..................................
5-9

REPORT: 2210
5-i
PIPER AIRCRAFT CORPORATION SECTION 5
PA-3lT, CHEYENNE PERFORMANCE

SECTION 5

PERFORMANCE

5.1 GENERAL

AII of the required (FAA regulations)and complementary performance

information applicable to the Cheyenne is provided in this section.

5.3 INTRODUCTION -

PERFORMANCE AND FLIGHT PLANNING

The performance information in this section is based on measured

Flight Test Data corrected to I.C.A.O. standard day conditions and analyti-
cally expanded for the various parameters of weight, altitude, temperature,
etc.

The performance charts are unfactored and do not make any allowance
for varying degrees of pilot proficiency or mechanical deterioration of the
airplane. This performance can, however, be duplicated by following the
stated procedures in a properly maintained airplane.

Effects of cond itions not considered on t he cha rts, such as t he effect of a

soft or grass runway surface on takeoff and landing performance, or the
effect of winds aloft on cruise and range performance, must be evaluated by
the pilot.

REMEMBER! To get chart performance, follow the chart procedures.

The information provided in item 5.5 (Flight Planning Example)

outlines a detailed flight plan using the performance charts in this section.
Each chart includes its own example to show how it is used.

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

5-1
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

THIS PAGE INTENTlONALLY LEFT BLANK

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-2
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

5.5 FLIGHT PLANNING EXAMPLE

The following Flight Planning Example illustrates the correct utili-

zation of pertinent data presented in this section of the manual.

(a) Associated Conditions

Certain basic information must be gathered when planning a
flight. This information includes departure and destination airport
conditions, en route conditions, and basic aircraft conditions. Such
factors as weather, the status of the runway, the distance of the
flight, the number of passengers, etc., must be determined. Assume,
for example, the following conditions:
(1) Departure Airport Conditions
Outside Air Temperature 17°C
Pressure Altitude 2000 ft.
Wind and Direction 15 kts at 360°
Runway Direction 300°

(2) Cruise Conditions.

Outside Air lemperaturc -7°C
Pressure Altitude 16,000 ft.
En route Distance 700 naut. mi.
Power Setting Maximum Cruise (2000 RPM)

(3) Destination Airport Conditions

Outside Air Temperature 20°C
Pressure Altitude 2000 ft.
Wind and Direction 10 kts at 330°
Runway Direction 270°

(4) Aircraft Configuration

Basic Weight (Assumed) 5070 lbs.
Fuel Tanks (Total usable) 366 gal.
Occupants 4 at 170 lbs. each
Baggage 227 lbs.

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

REVISED: FEBRUARY 6, 1984 5-3
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

(b) Aircraft Loading

The airplane weight and center of gravity may be determined by
utilizingthe information given in Section6(Weightand Balance) of
this handbook.

The basic empty weight for the airplane as delivered from the
factory has been entered in Figure 6-7. If any alterations to the
airplane affecting weight and balance have been made, reference to
the aircraft logbook and Weight and Balance Record (Figure 6-9)
should be made to determine the current basic empty weight of the
airplane.

Use the Weight and Balance Loading Chart (Figure 6-15) and
the Weight, Moment and C.G. Limit graph (Figure 6-17) to
determine the total weight of the airplane and the center of gravity
position.

After proper utilization of the information provided, assume

that the following weights have been determined for consideration
in the Flight Planning Example.
(1) Basic Weight 5070 lbs.
(2) Occupants (4 at 170 lbs. each) 680 lbs.
(3) Baggage 227 lbs.
(4) Fuel (366 gal. at 6.7 lbs/gal.) 2452 lbs.
(5) Ramp Weight (total of above) 8429 lbs.
(6) Landing Weight (takeoff weight minus
Item (h), Total Fuel Required) 6870 lbs.

The landing weight cannot be determined until the weightof the

fuel to be used has been established.

Ramp weight is below the approved maximum of 9050 lbs.

Determine that weight and balance calculations have shown the
C.G. position to be within the approved limits.

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-4 REVISED: FEBRUARY 6, 1984
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

(c) Takeoff Distance

After determining the aircraft loading, all aspects of takeoff
must be considered. Conditions of the departure airport and takeoff
weight should be applied to the appropriate Takeoff Distance graph
to determine the length of runway necessary. Takeoff conditions for
the Flight Planning Example are listed below:
(1) Wind 15 kts at 360°
-300°

(2) Angle between Flight Path and Wind 360° = 60°

(3) Head Wind Component (from Wind

Component Graph, Figure 5-15) 8 kts
(4) Outside Air Temperature 17°C
(5) Pressure Altitude 2000 ft.

Using the Normal Takeoff over 50 Feet graph (Figure5-25)the

takeoff distances are as follows:
Total Distance 1950 ft.
Ground Run 1450 ft.

(d) Climb
Entering the example conditions of the departure airport and
the cruise altitude into the ISA conversion graph (Figure 5-13) and
the Time, Fuel and Distance to Climb graph (Figure 5-45) yields the
following:
(I) Time to Climb 9.0 1.0 =
-

8.0 minutes
(2) Fuel to Climb .
90 20-
=
70 lbs.
(3) Distance to Climb 30.0 2.0 =
-

28.0 naut. miles

NOTE

The effect of winds aloft must be considered by

the pilot when computing climb, cruise, and
descent performance.

(e) Descent
Entering the cruise and destination airport conditions into the
Time, Fuel and Distance to Descend graph (Figure 5-167) yields the
following:
(1) Time to Descend 16 2
-
=
14 minutes
(2) Fuel to Descend 155 20
-
= 135 lbs.
(3) Distance to Descend 66 9-
=
57 naut. miles

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

REVISED: FEBRUARY 6, 1984 5-5
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

(f) Cruise
Subtracting the previously calculated distance to climb and
distance to descend figures from the total en route distance yields
the total cruise distance. For example:
Cruise Distance
=
En route Distance Climb Distance Descent Distance
- -

=
700 28.0 57.0
- -

=
615 naut. miles

From the Pressure Altitude vs. OAT Chart (Figure 5-13) and
the Power Setting Table (Figure 5-55) for Maximum Cruise (2000
RPM, ISA + 10°C) the cruise airspeeds are 272 kts. at 8000 lbs. and
276 kts. at 7000 lbs. Extrapolating these values for 7500 lbs.
(estimated average cruise weight), the cruise speed is 274 kts.
From the same table, Fuel Flow is 572 lbs.jhour (total)
Cruise time and fuel may be calculated by the following
formula:
Cruise Time
Cruise Distance/Cruise Speed
=

= 615/274

2.245 hours or 134.7 minutes

=

Cruise Fuel
= Fuel Flow
x Cruise Time
=
572 x 2.245
=
1284 lbs.

The above data can be used to verify the estimated average

cruise weight in the following manner:
Average Cruise Weight
=
Takeoff Weight (Ramp Fuel + Climb Fuel) Cruise Fuel
- -

2
= 8429 -

(65 + 70) -

1284

=
7652 lbs.

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-6 REVISED: AUGUST 28, 1980
PIPER AIRCRAFT CORPORATION SECTION S
PA-31T, CHEYENNE PERFORMANCE

From the Power Setting Table(Figure 5-55), thecruisespeed is

now 273 kts. for 7652 lbs. Applying the above cruise time and cruise
fuel formula results in the following figures:
Cruise Time
=
2.253 hours or 135.2 minutes

Cruise Fuel
=
572 x 2.253
=
1289 lbs.

(g) Total Flight Time

The total flight time is determined by adding the time to climb,
cruise time, and time to descend. The following flight time is
required for this Flight Planning Example:
Total Flight Time
=
Time to Climb + Cruise. Time + Time to Descend
=
8.0 + 135.2 + 14.0
=
I 57.2 minutes

(h) Total Fuel Required

Determine the total fuel required by adding fuel for taxi and
takeoff, fuel to climb, cruise fuel, and fuel to descend. When the
total fuel (in Ibs.) is determined, dividing this value by 6.7 will give
the total fuel in gallons to be used for the flight. Total fuel calcu-
lations for the Flight Planning Example are shown below:
Total Fuel Required
=
Fuel for taxi and takeoff + Fuel to Climb + Cruise Fuel +
Fuel to Descend
=
65 + 70 + 1289 + 135
=
I559 lbs. (232.7 gallons)

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

5-7
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

(i) Landing Distance

Subtracting the total fuel required from the takeoff weight of

the airplane gives the landing weight:
Landing Weight
=
Takeoff Weight Total Fuel Required
-

=
8429 1559
-

=
6870 lbs.

Destination airport conditions applied to the Wind Component

graph (Figure 5-15) gives the following head wind component for
the Flight Planning Example:
Theanglebetweentheflight pathand windis330°-270°or60°.
Therefore, the Head Wind Component is 5 kts.

From the Landing Distance over 50 Feet (with Reversing)

graph (Figure 5-175), with the destination airport conditions, the
distances required for landing for the Flight Plan Example are as
follows:
Total Distance 1580 ft.
Ground Roll 660 ft.

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-8 REVISED: FEBRUARY 6, 1984
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

5.7 PERFORMANCE ÖRAPMS

LIST OF FIGURES

Figure Page
No. No.

5-1 Airspeed Calibration Standard Static Source......... -

5-13
5-3 Airspeed Calibration Alternate Static Source......... -

5-14
5-5 Altimeter Calibration Standard Static Source -
........
5-15
5-7 Altimeter Calibration Alternate Static Source -
........
5-16
5-9 Cabin Altitude Vs. Airplane Altitude................. 5-17
5-Il Temperature Conversion............................ 5-18
5-l3 ISA Conversion ................................... 5-19
5-f5 Wind Components................................. 5-20
5-16 Maximum Demonstrated Crosswind Component Vs.
Wind Measurement Height .......................
5-20a
5-l7 Torque Vs. Shaft Horsepower .......................
5-21
5-19 Accelerate/Stop Distance........................... 5-22
5-21 Takeoff Power(Torque)............................ 5-23
5-23 Takeoff Power(Fuel Flow) .........................

5-24
5-25 Takeoff Distance Over 50 Feet . .
. . . . . . . . . . . . . . . . . . . .
5-25
5-27 Single-Engine Takeoff.............................. 5-26
5-29 Stall Speeds.................... .
.. ............. 5-27
5-31 Maximum Climb Power (Torque).................... 5-28
5-33 Maximum Continuous Power (Torque)............... 5-29
5-35 Maximum Continuous Power (FucI Flow) ............
5-30
5-37 Single-Engine Climb (Oil Cooler Door Closed
on Operative Engine)............................. 5-31
5-39 Single-Engine Climb (Oil Cooler Door Open
on Operative Engine)............................. 5-32
5-4! Twin-Engine Climb ................................
5-33
5-43 Twin-Engine Climb (SAS Override On). .
. .
. . . . . . . . . . .
5-34
5-45 Time, Fuel and Distance to Climb ...................

5-35
5-47 Maximum Cruise Power 2000 RPM ISA -30°C..... -

-2000
-

5-37
5-49 Maximum Cruise Power RPM ISA -20°C..... -

5-38
5-51 Maximum Cruise Power - 2000 RPM ISA -10°C..... -

5-39
5-53 Maximum Cruise Power 2000 RPM ISA........... - -

5-40
5-55 Maximum Cruise Power 2000 RPM ISA +IO°C -

-2000
-
....
5-41
5-57 Maximum Cruise Power RPM ISA +20°C -

....
5-42
5-59 Maximum fruise Power 2000 RPM ISA +30°C - -
....
5-43
5-61 Maximum Cruise Power 2000 RPM ISA +37°C - -

.... 5-44
5-63 Maximum Cruise Power 1900 RPM ISA -30°C..... - -

5-45

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

REVISED: DECEMBER I, 1983 5-9
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-3lT, CHEYENNE

Figure Page
No. No.

5-65 Maximum Cruise Power 1900

ISA -20°C.....
-

RPM -

5-46
5-67 Maximum Cruise Power -

1900
ISA -10°C..... RPM -

5-47
5-69 Maximum Cruise Power -

1900
ISA........... RPM -

5-48
5-71 Maximum Cruise Power ISA +10°C
-

1900 RPM -

.... 5-49
5-73 Maximum Cruise Power ISA +20°C
-

1900 RPM -

.... 5-50
5-75 Maximum Cruise Power ISA +30°C
-

1900 RPM -

....
5-51
5-77 Maximum Cruise Power ISA +37°C
-

1900 RPM -

....
5-52
5-79 Economy Cruise Power -

2000 RPM
ISA -30°C...... -

5-53
5-81 Economy Cruise Power -
2000 RPM
ISA -20°C...... -

5-54
5-83 Economy Cruise Power -

2000 RPM
ISA -10°C...... -

5-55
5-85 Economy Cruise Power -

ISA 2000 RPM -

........... 5-56
5-87 Economy Cruise Power -

ISA +10°C 2000 RPM -

..... 5-57
5-89 Economy Cruise Power -

ISA +20°C 2000 RPM -

.....
5-58
5-91 Economy Cruise Power -

ISA +30°C 2000 RPM -

..... 5-59
5-93 Economy Cruise Power -

ISA +37°C 2000 RPM -

.....
5-60
5-95 Economy Cruise Power -

1900 RPM
ISA -30°C...... -

5-61
5-97 Economy Cruise Power -

1900 RPM
ISA -20°C...... -

5-62
5-99 Economy Cruise Power -

1900 RPM
ISA -10°C...... -

5-63
5-101 Economy Cruise Power -

ISA 1900 RPM -

........... 5-64
5-103 Economy Cruise Power -

ISA +10°C 1900 RPM -

..... 5-65
5-105 Economy Cruise Power -

ISA +20°C 1900 RPM -

..... 5-66
5-107 Economy Cruise Power -

ISA +30° C 1900 RPM -

. . . . . 5-67
5-109 Economy Cruise Power -

ISA +37°C 1900 RPM -

..... 5-68
5-111 Maximum Range Power -

1900 RPM
ISA -30°C..... -

5-69
5-113 Maximum Range Power -

1900 RPM
ISA -20°C..... -

5-70
5-115 Maximum Range Power 1900 RPM ISA -10°C.....
- -

5-71
5-117 Maximum Range Power 1900 RPM -

ISA........... -

5-72
5-119 Maximum Range Power 1900 RPM -

ISA +10°C -

.... 5-73
5-121 Maximum Range Power 1900 RPM
-

ISA +20°C -

.... 5-74
5-123 Maximum Range Power 1900 RPM
-

ISA +30°C -

. ..
5-75
5-125 Maximum Range Power 1900 RPM
-

ISA +37°C -

.... 5-76
5-127 Single-Engine Cruise Power 2000 RPM ISA -30°C - -

.. 5-77
5-129 Single-Engine Cruise Power 2000 RPM ISA -20°C
- -

..
5-78
5-131 Single-Engine Cruise Power 2000 RPM ISA -10°C
- -

.. 5-79
5-133 Single-Engine Cruise Power 2000 RP M ISA - -

. . . . . . . . 5-80
5-135 Single-Engine Cruise Power 2000 RPM ISA +10°C..
- -

5-81
5-137 Single-Engine Cruise Power 2000 RPM ISA +20°C.. - -

5-82
5-139 Single-Engine Cruise Power 2000 RPM ISA +30°C..
- -

5-83
5-141 Single-Engine Cruise Power 2000 RPM ISA +37°C.. - -

5-84

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-10
 PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

Figure Page
No. No.

5-143 Specific Range Maximum Cruise Power

-8000
- -

2000 RPM Lbs. .............. ............

5-85
5-145 Specific Range Maximum Cruise Power
-8000
- -

1900 RPM Lbs. ...........................

5-86
5-147 Specific Range Economy Cruise Power
-8000
- -

2000 RPM Lbs. ...........................

5-87
5-149 Specific Range Economy Cruise Power
-8000
- -

1900 RPM Lbs. ...........................

5-88
5-151 Specific Range Maximum Range Power
-8000
- -

1900 RPM Lbs. ...........................

5-89
5-153 Speed Vs. Altitude................................. 5-91
5-155 Maximum Operating Speed .........................
5-92
5-157 Single-Engine Service Ceiling. . .
. . . . . . . . . . . .
. .
. . . .
. . .
5-93
5-159 Endurance Profile ---..............................

5-94
5-161 Range Profile .....................................

-7000
5-95
5-163 Holding Time Lbs............................
-9000
5-96
5-165 Holding Time Lbs............................ 5-97
5-167 Time, Fuel and Distance to Descend . . . . . . .
. . . .
. . . . . .
5-98
5-169 Balked Landing Climb .............................

5-99
5-171 Balked Landing Climb (SAS Override On)............ 5-100
5-173 Landing Distance Over 50 Feet (Without Propeller
Reversing) ......................................
5-101
5-175 Landing Distance Over 50 Feet (With Full Propeller
Reversing) ..................... ................ 5-102
5-177 Landing Distance Over 50 Feet (SAS Override On) .... 5-103
5-179 Short Field Landing Dista nce Over 50 Feet . . . . .
. .
. . .
.
5-104

. ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

REVISED: FEBRUARY 6, 1984 5-11
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-12 REVISED: FEBRUARY 6, 1984
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

PA-31T
littlihtttfi‡††‡t‡i‡t‡‡ißliltilllllilll
AIRSPEED CALIBRATION
..

STANDARD STATIC SOURCE

WI H RDR-12OO OR AVO-21 RADOME

NOTE
INDICATED AIRSPEED
ASSUMES ZEHO INSTRU
MENT ERROR

EMMlli
Example:
Indicated airspeed: 130 knots
Flaps: 0°
Calibrated airspeed: 134 knots

250

200

nn T
it it ( 150 200
"
INDICATED AIRSPEED -
KTS

AINSPEED CALIBRATION -

STANDARD STATIC SOURCE

Figure 5-I

ISSUED: SEPTEMBER 14, 1979 REPORT: 22f0

5-13
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T,CHEYENNE

PA-31T
'Näã ëëõ·õXüähätiön"
ALTERNATE STATIC SOURCE
W 1DR-1200 OR AVO-21 RA 1F1E

INDICATED
BRUS
NOTE
AIRSPEED
ASSUMES ZERO INSTRU-
-

EN ANO

Example:
Indicated airspeed: 140 knots
Flaps: 0°
Calibrated airspeed: 140 knots

250

200

tu

1so

100

L( 1 200
INDICATED AIRPSEED -

KTS

AIRSPEED CALIBRATION -

ALTERNATE STATIC SOURCE

Figure 5-3

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-14
 PA-31T
ALTIMETER CALIBRATION
STANDARD STATIC SOURCE
WITH RDR-1200 OR AVO-21 RADOME
POSITION ERROR CORRECTION TO OßTAIN CALIBR ED ALTITUDE

100
nnn

E L Example:
000 indicated airapeed: 125 knots
Flaps 40°
-100
Pressure altitude: sea level
Altimeter correction (subtract from
-20

indicated altitude): ft.

I

00 1
o 130 150 170 190 210 230 260
INDICATED AIRSPEED --

KTS
 PA-31T
ALTIMETER CALIBRATION -

ALTERNATE STATIC SOURCE

WITH RDR-1200 OR AVQ-21 AADOME
POSITION ERROR CORRECTION TO OBTAIN CALIBRATED ALTITUDE

..
NOTE
INDICATED AIRSPEED AND
ALTITUDE ASSUME ZERO
INSTRUMENT ENHOR.

Example:
+400
Indicated airspeed: 185 knots
Flaps: O
Pressure altitude: 10,000 ft.
Altimeter correction (subtract from
-120

+200
indicated altitude): ft

FLAPS RETRACTED
FLAPS EXTENDED

BEA LEVEL
-200
10000 FT
SEA LEVEL
loooO FT.

20000 FT.
-4

90 110 130 1EO 170 100 210 230 250

INDICATED AIRSPEED --

KTS
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

w
Q

...I
4
m
z

I- n:

i
I i li ID

i ! il

CABIN ALTITUDE VS. AIRPLANE ALTITUDE

Figure 5-9

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

5-17
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

40
100

90
30
80

70
20

60

50 10

40
FAHRENHEIT CELSIUS
30 O
DEGREES DEGREES
20
-10

10

0 -20

-10

-20

-30

-30

-40 -40

TEMPERATURE CONVERSION
Figure 5-1 I

REPORT: 2210 ISSUED: SEPTEMBER 14 1979

5-18
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T,CHEYENNE PERFORMANCE

ISA CONVERSION
ääüWë'Etifübe
Vs.
ilT3ICE AIR TEMPERATI i
I

M 14TLR -°F

31000

25000

I 20000

isooo

10000
IL

6000

0 -40 -30 -20

+13
-7) -It +10 +20 +30
- C 0 +EL
-10
TEMPERATURE - °C

ISA CONVERSION
Figure 5-13

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

5-19
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

}¾tm
PA-31T
‡¾}}}Hilfl#ii
}
WIND COMPONENTE

NOTE
DEMONSTRATED CROSSWIND COMPONENT
FOR LANDING 18 16 KTS. THIE WAS THE MAxi-
-

MUM CROSSWIND COMPONENT AVAILABLE

DURING FAA CI NTI. ICATION BUT IS NOT CON-
SIDERED A LIM TA1 ON

ANGLEBETREEí IIÍHTPATHANDWI i -I ÉSM

60 I
Example.
Wind velocity: 30 knots
Angle between flight path and wind: 30
Headwind component: 26 knots
40
Crosswind component: 5 knots

20

0 30 10 50
COOf SSWIND COMP)fD KTS.

WIND COMPONENTS
Figure 545

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-20 REVISED: AUGUST 28, 1980
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

so ,,,,,,,,, ,,,......., ,,,,,,

PA-31T
,,,, , ,,,,,,,,,,,,,,,, ,,

MAXIMUM DEMONSTRATED
CROSSWIND COMPONENT
45
VS.
NIND MEASUREMENT HEIGHT
40 -

O
E 35

30

m 20

10

0 -s

10 20 30
MAXIMUM DEMONSTRATED CROSSWlND COMPONENT -
KTS.

MAXIMUM DEMONSTRATED CROSSWIND COMPONENT

VS.
WIND MEASUREMENT HEIGHT
Figure 5-16

ISSUED: DECEMBER 1, 1983 REPORT: 2210

5-20a
SECTION 5 PlPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

THIS PAGE INTENTIONALLY LEFT BLANK

REPORT: 2210 ISSUED: DECEMBER 1, 1983

5-20b
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

Id 81 -

300801

TORQUE VS. SHAFT HORSEPOWER

Figure 5-17

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

5-21
 PA-31T
ACCELERATE/STOP DISTANCE ex.mpi.
OAT: 10°C
ASSOCIATED CONDITIONS:
TAKE-OFOOWER,FLAPS Pressure altitude: 2000 ft
0°, ANTI-tCE OFF
- -

SPEED 91 KIAS,BRAKING MAXIMUM - Weight: 8400 lbs

NO ENGINE REVERSING RUNWAY DRY PAVED SURFACE
-
Wind: +10 knots
Accelerate -

stop distance: 3025 ft

NOTE
DISTANCES INCLUDE A FAILURE
RECOGNm0N TIME OF THREE o 6000
SECONDS

2000

-30 -20 -10 tooo < >

0 10 20 30 40 60 0000 8000 7000 0 10 20 30 My
OUTSIDE AIR TEMP. -°C WEIGHT LBS. WIND COMPONENT KTS.
y Q
- -
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEVENNE PERFORMANCE

PA-31T
TAKE-OFF POWER
220) IPM 70 KTS CALIBF ATED AIRSPEED
H i HH I itTiHiHH tHHttlHi
TIIE t IW ER (T R 1UE) INDICAT ËI IS THE MINIMUM
V.4L EV ITH WIIM 11THE TAK PERFORMANC
10 T I ECTI N 3AN BE f

1500

1400

1300

1200

1100

1000

TAKEOFF POWER (TORQUE)

Figure 5-21

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

5-23
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-3lT, CHEYENNE

PA-31T
TMä ä ¥ FäWà
L IO 10

450

400

soo

'
250

TAKEOFF POWER (1 UEI FLOW)

Figun: 5-23

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-24
 PA-31T
TAKE-OFF DISTANCE OVER 60 FT.
ASSOCIATED CONDITIONS:
PAVED.LEVEL, DAY, RUNWAY FLAP SETTING 0
TAKE-OFF POWER. ANTI-ICE OFF 6000
ROTATION SPEED 91 KIAS. BARRIER SPEED 102 KIAS
xample:
OAT: 10°C
Pressure altitude: 2000 ft coco
Weight: 8400
Wind: +10 knots
Ground roll: 1350 ft.
Distance over 50 ft 1850 ft 4000

1000

-30 -20 -10 0

0 10 20 30 40 50 9030 8000 7000 « 10 20 30 e 53
OUTSIDE AIR TEMP. -
°C WEIGHT -

LBS. WIND BA tRIER -

FT.
COMPONENT -

KTS.

2
 PA-31T
ASSOCIATED CONDITIONS
POWER TAKE-OFF FLAPS 0° SINGLE ENGINE TAKE-OFF
INOPERATIVE ENGINE PROP. FEATHERED
ANTI-ICE OFF 7000 2
RUNWAY DRY PAVED SURFACE
NOTE HATCHED AREA DOES NOT
IF ENGINE FAILURE OCCURSAT 91 KIAS OR ABOVL MAINFAIN PROVIDE POSITIVE CUMB RATE
DIRECTIONAL CONTROL WITH NOMEWHEEL STEEllING AND IM
WITH GEAR EXTENDED. &
MEDIATELY FEATHER PROPEi.LER ON DEAD ENGINE. COM
MENCE NOTATION AT OR ABOVE 91 KIAS. ACCELENATE TO 104 00
KIAS UNTIL OBETACLES ARE CLEAREDAND CLIMB AT 113 KlAB
FOR IMPROVED OBSTACLE CLEARANCE RETRACT LANDING
GEAN WHEN POSITIVE CLIMB RATE ESTABLISHED. ABORT TAKE-
OFF IF ENGINE FAILURE CCUNS BEL W 91 KI .

sooo

3000

ISA 2000

-30 -20 501000

-

O 10 2 30 40 50 9000 8000 7000 0 10 20 30 0

OUTSIDE AIR TEMP. -

*C WEIGHT- LBS. WIND COMPONENT BARRIER -

FT. 2 ..

KTS.
-

2
 PA-31T
STALL SPEEDS
IDLE POWER,FORWARD C.G.
I
NOTE
1 MAxlMUM ALTITUDE LOSS DURING STALL RE-
COVERY IS APPROXIMATELY 750.
MAxlMUM NOSE DOWN PITCH ATTrTUDE LOSS DUR
1NG RECOVERY FROM SINGLE ENGINE STALLS ARE
APPROXIMATELY 15* AND 700 FT. RESPECTIVELY. I
3 LANDINGGEARPOSITIONHASNOEFFECTONSTALL
PElm.

140
Example:
night A 1 lhy.
Opl
nir hr 120
KIAS: 78

CAUBRATED
--
100 u
INDICATED ---

EO
50 a
sooo sooo 7000
o lo 20 3o 4o ao a
WEIGHT -
POUNDS ANGLE OF BANK -

DEGREES 2
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-3IT, CHEYENNE

PA-31T
MAXIMUM CLIMB POWER

1600

1200

1000

soo

soo

400

MAXIMUM CI IMB POWER (TORQUE)

Figure 5-31

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-28
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

PA-31T
EfüniMúñ ääniiküöus
2200 RPM
ëök
.
n * 4 BALKED LAF lin G Gli 18 O W'
1500

uoo

noo

1200

11oo

looo

aoo
o,

700

600

MAXIMUM CONTINUOUS POWER (TORQUE)

Figure 5-33

ISSUED: SEPTEMBER 14, 1979 HEPORT: 2210

REVISED: MARCH 20, 1980 5-29
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-3lT, CHEYENNE

PA-31T
MAX1MUM CC MT MUOUS POWER
SINGLE ENGINE AND I di KE : LANDING CLIMBS ONLY
300 0 *M

4 -

400

*,
350 1 + .

300

260

200

100

MAXIMUM CONTINUOUS POWER (FUEL FLOW)

Figure 5 35

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

540
 PA-31T
-

::
SINGLE ENGINE CLIMB
ASSOCIATED CONDITONS: Example:
MAXIMUM CONTINUOUS POWER OAT: +10°C
PROPELLER FEATHERED ON INOPERATIVE ENGINE : Tooo
Pressure altitude: 4000 ft.
OIL COOLER DOOR CLOSED ON OPERATIVE ENGINE.
GEAR RETRACTED FLAPS 0. : Weight: 8500 Ibs.
CLIMB SPEED 113 (IAS : Rate of climb: 640 F.P.M.

oc

37.8 DAY

I -400 2
Ô Z
-53 -40 -30 -20 -10

0 10 20 30 40 50 9000 8600 8200 7800 7400 70 JO

-
e | -
o
OUTSIDE AIR TEMP. -°C WEIGHT -

LBS.
 PA-31T
SINGLE ENGINE CLIMB
ASSOICATED CONDITIONS:
MAXIMUM CONTINUOUS POWER 800
PAOPELLER FEATHERED ON INOPERATIVE ENGINE
Example: OIL COOLER DOOR OPEN ON OPERATIVE ENGINE
OAT: +35°C GEAR RETRACTED, FLAPS O
IMB SPEED 3 KIAS
Pressure attitude: 400 ft 00
Weight: 8500 Ibs
Rate of climb: 220 F.P M

400
N 2

200

-400

-20 -10

30 40 60 9000 8500 8000 7600 7000

30 0 10 20
OUTSIDE AIR TEMP. -*C WEIGHT --

LBS.
 PA-31T
TWIN ENGINE CLIMB
ASSOCIATED CONDITIONS:
MAXIMUM CLIMB POWER
GEAR AND FLAPS RETRACTED
Example: OIL COOLER DOORS CLOSED
OAT: +10°C CLIMB SPEED 121 KIAS
Pressure altitude: * A- 2000 RPM
Weight: 8600 lbs. 3500
- -
Rate of climb: 2260 F.P.M.

sooo

2soo

2000 O
ud

0 -
1500

-30 -20 -10

1000
0 10 20 30 40 60 9000 8600 8000 7E00 7000
OUTSIDE AIR TEMP. -

C WEIGHT -

LBS
 PA-31T
TWIN ENGINE CLlMB
ASSOCIATED CONDITIONS:
(SAS OVERRIDE ON 400 SNP LIMIT)
GEAR AND FLAPS RETRACTED
OIL COOLER DOORS CLOSED
Example: 1 CLIMB SPEED 121 KtAS
OAT: +5°C
Pressure altitude: 5000 ft 2500
Weight: 8400 lbs.
Rate of climb: 1380 F.P.M.

2ooo

SEALEVEL
2000
nog isoo

IsA looo

-30 -20 -10 O

0 10 20 30 40 60 9000 8000 7000
OUTSIDE AIR TEMP. ---

*C WEIGHT -

LBS.
 PA-31T
TIME, FUEL AND DISTANCE TO CLIMB
MAXIMUM CLIMB 00 RPM

0
Example:
25000 Altitude: 22,000 ft.
Weight: 9000 lbs.
Temperature: ISA +20°C ALTCLIUMBESPEED
SCHESDULE
20000
Time to climb: 22 minutes
S.L. 20000
-

FT. 135
16000 20000 24000
-

117
24000-31000 109

10000

5000

o
ISA REFERENCE UNE .

ISA +10°C

ISA +20°C

ISA +30°C

O 20 40 60 80 0 100 200 300 400 0 50 100 150 200

TIME TO CLIMB -
MIN. FUEL TO CLIMB -

LBS. DISTANCE TO CLIMB -

NAUT. ML
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-3IT, CHEYENNE

TillS PAGE INTENTIONALLY LEFT 81 ANK

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-36
 MAXIMUM CRUISE POWER • 2000 RPM • ISA -30°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude 10/T Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb./ Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level

2000

4000 FOR VALUE BELOW 10,000 FT. REFER TO ECONOMY CRUISE POWER TABLES.

6000

.. 8000
e
-26 -32

10,000 1628 361 722 244 268 246 270 246 270
-33 -36

12,000 1628 360 720 241 273 244 276 246 278
-40 -40

14,000 1628 358 716 238 278 24! 282 244 285
-47 -44

16.000 1575 346 692 232 280 235 284 238 287
-54
-48
18.000 1485 323 646 223 278 227 282 230 287
-61 -52

20,000 1380 303 606 213 274 216 278 220 283
-69 -56

22,000 1285 28 I 562 203 270 208 276 2 I2 28 I

-76 -60

24,000 1180 258 516 192 264 197 271 202 277
-85 -65

o 26,000 1065 236 472 180 256 185 263 189 270

i
-98 -72

29.000 820 196 392 150 226 156 235 163 245
-107 -77

31,000 660 165 330 I18 184 132 206 141 220 2
 MAXIMUM CRUISE POWER •
2000 RPM • ISA -20°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb.Ft. Lb.:Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level

2000

4000 FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.
6000

8000
-22

10.000 -

8 1628 361 722 242 27] 245 274 246 275 ag

-15 -26

12.000 1628 361 722 239 276 242 280 245 283
' -22 -30

e 14.000 1600 354 708 235 279 238 284 24] 287
-29 -34

16.000 1495 333 666 226 278 228 28] 231 284
-36 -38

18.000 1405 312 624 216 275 220 279 223 283
-43 -42

20.000 1315 292 584 206 27\ 210 276 214 28]
-51
-46

22.000 1220 272 544 196 267 201 273 205 279
-58 -50

24.000 1130 252 504 186 261 191 268 195 275
-67 -55

26.000 1035 23] 462 175 256 181 263 186 270
-80 -62

29.000 865 201 402 154 235 159 245 166 255
-89 -67

31.000 740 179 358 134 213 14! 225 149 237 2 Q
 •2000
MAXIMUM CRUISE POWER RPM • ISA -10°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level

2000

4000 FOR VALUES BELOW 10,000 FT. REFER TO ECONOMY CRUISE POWER TABLES.

6000

8000
-12

10,000 10 1628 363 726 24] 275 243 278 246 281
-16

12.000 3 1615 360 720 236 278 240 283 245 289
-20

14.000 -

4 1525 340 680 228 277 231 28] 235 285

-13 -25

16.000 1420 320 640 218 274 221 279 225 283
-20 -29

18,000 1340 298 596 208 271 213 276 216 281
-27 -33

20,000 1245 278 556 200 268 204 273 208 280
-39 -39

22,000 1180 260 520 191 266 196 272 200 277
-42 -41

24.000 1105 242 484 182 261 187 268 l91 275
-49 -45

26.000 1010 227 454 170 254 175 261 181 269
-61 -52

29.000 880 202 404 153 240 159 251 165 259
-69 -57

3l.000 780 185 370 139 227 146 238 153 250
 MAXIMUM CRUISE POWER • 2000 RPM • ISA
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TA S
Sea Level

2000
4000 FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.

6000

8000

10.000 28 -

2 1628 365 730 238 277 241 281 244 285

12.000 21 -

6 1535 344 688 23I 277 235 281 238 286

-10

14.000 14 1445 322 644 222 274 226 279 229 284
-14

16.000 7 1350 304 608 212 271 216 277 220 28!
-18

18.000 0 1260 284 568 202 267 207 273 211 279
-23

20.000 -
9 1180 265 530 192 262 096 269 202 276
-17 -27

22.000 I 100 248 496 182 258 188 266 193 273
-24 -31

24.000 1040 232 464 172 253 t74 262 184 270
-35

26.000 -3I 960 217 434 163 248 169 257 175 267
-42 -4]

29,000 870 196 392 149 240 156 250 162 261
-53 -47

31.000 795 176 352 138 229 146 242 152 253
 MAXIMUM CRUISE POWER • 2000 RPM • ISA +10°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb.!Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level
2000

4000 FOR VALUES BELOW 10,000 FT. REFER TO ECONOMY CRUISE POWER TABLES.

6000

8000

10,000 46 8 1525 342 684 230 273 234 277 236 279

I2.000 39 4 1430 322 644 221 271 225 275 228 279

14.000 32 0 1350 304 608 212 268 216 274 220 278
16.000 23 -

5 1260 286 572 202 265 208 272 211 276

18.000 16 -

9 1180 268 536 193 261 198 268 202 273

-13

20.000 8 1105 25l 502 184 258 189 265 194 271
-!7

22.000 1 1035 237 474 I75 254 18I 261 186 268
-21

24,000 -

6 970 222 444 166 249 172 258 177 266

-13 -25

26.000 905 208 416 156 243 162 253 168 262
-26 -32

29.000 825 188 376 142 235 150 248 157 259
-35 -37

3l.000 790 175 350 132 224 140 238 149 253
 •2000
MAXIMUM CRUISE POWER RPM• ISA +20°C mm
Pressure Torque Fuel Flow Total Airspeed -

KTS Og
Altitude IO/.T Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 700C Lb. 2
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level

2000

4000 FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.

6000

8000

10.000 64 18 1390 321 642 219 264 223 269 227 274

12.000 57 14 13l5 302 604 211 263 215 268 219 273

14.000 49 9 1235 285 570 202 260 207 266 210 270

16,000 41 5 I 155 268 536 193 256 198 263 202 268

N 18.000 34 I 1090 252 504 184 254 189 261 194 266

m i 20,000 27 -

3 1025 236 472 175 250 181 257 186 264

-
22.000 19 -

7 960 222 444 166 245 172 254 177 261

-12

24,000 II 895 208 416 156 240 162 248 168 258
-16

26.000 3 840 194 388 147 233 154 244 160 256
-22

29.000 -

8 760 178 356 130 218 14 l 235 148 248

-17 -27

31.000 715 168 336 120 208 130 225 138 239 2
 MAXIMUM CRUISE POWER • 2000 RPM • ISA +30°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb.. Hr. CAS TAS CAS TAS CAS TAS
Sea Level

2000

4000 FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.

6000

8000

10.000 82 28 1285 302 604 210 258 215 263 219 268

12.000 75 24 1215 284 568 202 256 206 261 210 267

14.000 66 19 I 145 268 536 193 253 198 259 205 265

16.000 59 15 1075 252 504 184 249 189 256 195 263 ,

18.000 52 11 10\0 236 472 175 247 181 254 186 26l

20.000 45 7 950 222 444 167 242 173 251 178 259

22.000 37 3 895 208 416 158 238 164 248 169 256

24.000 29 -

2 835 194 388 148 232 155 242 16] 252

26,000 21 -

6 780 182 364 137 222 146 236 153 248

-12

29.000 10 705 167 334 120 205 13\ 225 141 241
-!7

31.000 I 655 160 320 120 213 132 234 2

- -
 °
MAXIMUM CRUISE POWER 2000 RPM• ISA +37°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude 107 T Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb. 2
-
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Br. CAS TAS CAS TAS CAS TAS
Sea Level

2000

4000 FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.

6000

8000

10.000 93 34 1220 290 580 204 254 209 259 212 263
e 12.000 86 30 1140 272 544 195 250 200 256 204 261

14.000 79 26 1075 256 512 186 248 19I 254 195 260

16.000 72 22 1010 240 480 178 244 182 250 188 257

18.000 64 18 945 226 452 168 240 174 247 179 255

20,000 56 13 895 212 424 159 235 165 244 17! 252

22.000 48 9 840 198 396 151 230 158 241 164 249

24.000 41 5 790 185 370 142 224 149 236 156 247

26.000 34 1 735 173 346 123 212 139 228 148 241

29.000 21 -

6 655 158 316 - -

120 208 133 230

-11

31.000 12 600 148 296 - - -

120 216
-
 MAXIMUM CRUISE POWER • 1900 RPM • ISA -30°C

Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS

FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.
-26 -32

10,000 1628 350 700 238 261 24l 264 244 268
-33 -36

12.000 1628 348 696 235 265 238 269 241 272
-40 -40

14,000 1628 346 692 231 270 235 273 237 277
-47 -44

16.000 1590 338 676 226 272 229 276 233 28 ] y

-54 -48

18.000 1495 315 630 217 270 22l 276 225 28]
-61 -52

20,000 1385 294 588 206 265 210 270 214 275
-69 -56

22.000 L280 272 544 196 26 I 20 I 267 204 272

-76 -60

24.000 I 170 249 498 184 254 189 261 l94 267
-85

26.000 65 1050 226 452 171 244 177 253 182 259
-98 -72

-
29.000 800 190 380 140 2I I 149 223 158 237
-107

31,000 -77 660 170 340 114 179 128 200 138 215 N
 MAXIMUM CRUISE POWER • 1900 RPM • ISA -20°C

Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb, 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS

FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.
-22

10.000 -

8 1628 356 712 236 265 239 268 241 270

-15 -26

12.000 1628 356 712 233 268 236 273 239 276
-22 -30

14.000 1628 354 708 229 274 234 279 236 282
-29 -34

16.000 1520 326 652 220 270 224 275 227 279
-36 -38

18.000 1425 305 610 210 267 215 273 218 277
-43 -42

20.000 1325 284 568 200 263 205 270 209 274
-51 -46

22,000 1220 264 528 189 257 195 264 199 270
-58 -50

24.000 1125 244 488 179 252 184 259 188 265
-67
-55

26.000 1025 222 444 168 244 174 253 179 261
-80
-62

29.000 840 19] 382 145 224 153 236 159 245
-67
-89
31.000 700 174 348 116 185 132 211 142 226
 MAXIMUM CRUISE POWER • 1900 RPM •ISA -10°C

Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS

FOR VALUES BELOW 10,000 FT. REFER TO ECONOMY CRUISE POWER TABLES.
-12

10.000 10 1628 359 718 234 267 236 270 240 274
-16

12.000 3 1628 356 712 231 272 235 276 237 280
-20

14.000 -

4 1555 336 672 223 272 227 276 230 280

-13 -25

16.000 1445 315 630 214 268 217 273 22] 277
-20 -29

I8.000 1360 292 584 204 265 209 271 212 275
-27 -33

20,000 1255 272 544 194 260 199 267 202 272
-35 -37

22,000 I 185 253 506 184 256 189 263 194 270
-42 -41

24,000 1105 235 470 175 253 181 260 185 266
-49 -45

26.000 1005 219 438 163 243 170 253 175 254
-6 -52

29,000 I 865 194 388 142 222 15 I 237 158 248

-69 -57

31.000 760 180 360 126 206 136 222 145 237
 MAXIMUM CRUISE POWER • 1900 RPM • ISA

Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS

FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.

10,000 28 -

2 1628 365 730 233 271 236 274 239 278

-

12,000 21 -

6 1580 341 682 227 272 229 275 233 280

-10

14,000 14 1485 318 636 218 270 221 273 225 279
-14

16.000 7 1380 300 600 207 266 212 272 215 276

18.000 0 -I8 1280 280 560 199 263 202 268 206 273
-23

20.000 -

9 1195 260 520 188 258 193 264 197 271

-17 -27

22,000 [115 243 486 178 253 183 260 188 267
-24 -31

24.000 1045 227 454 168 248 175 256 180 264
-31 -35

26,000 960 211 422 159 243 166 252 171 260
-43 -42

29.000 870 190 380 [45 233 152 244 158 254
-53 -47

31.000 790 178 356 130 216 139 231 148 246
 MAXIMUM CRUISE POWER • 1900 RPM • ISA +10°C

Pressure Torque Fuel Flow - Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS

FOR VALUES BELOW 10,000 FT. REFER TO ECONOMY CRUISE POWER TABLES.
10,000 46 8 1580 341 682 228 269 231 274 234 277

12,000 39 4 1475 320 640 219 268 222 272 226 276

, 14.000 32 0 1390 302 604 209 265 214 270 217 274

16.000 23 -

5 1295 283 566 200 261 205 268 208 272

18.000 16 -

9 1205 265 530 189 256 195 263 199 269

-13

20,000 8 I 125 247 494 180 252 185 259 189 266
-17

22.000 I 1050 233 466 170 247 176 256 182 262
-21

24.000 -

6 980 217 434 160 24l 168 25l 173 260

-13 -25

26.000 910 203 406 150 234 159 248 163 254
-26 -32

29,000 825 182 364 133 219 145 235 150 248
-35 -37

31.000 770 170 340 12] 205 135 229 141 239
 MAXIMUM CRUISE POWER • 1900 RPM • ISA +20°C

Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS

FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.
10.000 64 I8 1445 32 I 642 2 I7 262 22 I 262 224 270

12.000 57 14 1360 301 602 209 260 213 265 215 268

14.000 49 9 1280 284 568 200 257 204 262 207 266

16,000 41 5 1190 266 532 190 253 195 259 198 263

18.000 34 I 1120 250 500 181 248 186 256 190 261

20,000 27 -

3 1050 234 468 17\ 244 176 25\ 182 259

22,000 19 -

7 980 219 438 161 238 168 248 173 256

-12

24.000 11 910 205 410 152 233 158 242 164 251
-16

26.000 3 850 189 378 141 223 148 236 154 246
.
-22

29,000 -

8 760 173 346 121 202 135 227 142 237

-17 -27

31.000 700 163 325 --- -

121 21I 130 226

 MAXIMUM CRUISE POWER •
1900 RPM • ISA +30°C

Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS

FOR VALUES BELOW 10,000 FT. REFER TO ECONOMY CRUISE POWER TABLES.
10.000 82 28 1340 303 606 209 256 212 260 219 264

12.000 75 24 1270 285 570 200 254 203 258 208 263

14.000 66 19 1190 268 536 191 250 195 256 200 261
e
16.000 59 15 1115 252 504 182 246 187 253 191 259

18.000 52 11 1045 235 470 173 242 178 250 182 256
20.000 45 7 980 221 442 164 239 170 248 175 255
22.000 37 3 920 206 412 155 235 161 244 166 251

24.000 29 -

2 855 192 384 145 227 151 235 156 244

26,000 21 -

6 795 180 360 132 214 141 228 148 239

-12

29.000 10 700 164 328 - -

124 213 134 230
-17

31.000 I 630 155 3\0 - - -

122 216
-
 MAXIMUM CRUISE POWER •
1900 RPM • ISA +37°C

Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
F1. °F °C Lb. Ft. Lb. Hr. Lb./Hr. CAS TAS CAS TAS CAS TAS

C FOR VALUES BELOW 10.000 FT. REFER TO ECONOMY CRUISE POWER TABLES.
pum

10.000 93 34 1280 292 584 203 253 208 258 21 I 263

12.000 86 30 1195 274 548 195 249 198 255 203 261
14.000 79 26 1125 257 514 184 245 189 251 193 257

16.000 72 22 1055 241 482 175 241 180 247 185 257

18.000 64 18 980 226 452 166 237 17] 243 176 251

20.000 56 13 925 212 424 157 231 163 240 168 248

22.000 48 9 870 197 394 148 227 155 237 160 244

24.000 41 5 815 184 368 138 219 146 230 152 24]

26.000 34 I 750 171 342 124 203 134 219 142 233

29.000 21 -

6 665 155 310 - - - -

127 220

31.000 12-II 600 145 290 - - -

I14205
-
 ECONOMY CRUISE POWER •2000
RPM • ISA -30°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb.: Hr. CAS TAS CAS TAS CAS TAS
-13

Sea Level 9 1628 391 782 246 233 246 233 246 233
-17

2000 I I628 385 770 246 241 246 241 246 24l
-21

4000 -

6 1628 380 760 246 248 246 248 246 248

-l3 -25

-
6000 1628 375 750 246 255 246 255 246 255
-18 -28

8000 1628 371 742 246 261 246 261 246 261
-26 -32

10.000 1628 367 734 244 268 246 270 246 270
-33 -36

12.000 1540 345 690 236 268 239 270 241 273
-42 -41

14.000 1450 325 650 227 265 230 269 233 272
-49 -45

16.000 1360 305 610 218 262 221 268 225 27l
-56 -49

18.000 1280 286 572 209 26] 214 267 217 270
-63

20.000 -S3 12!0 268 536 20 \ 258 205 264 209 269
-71 -57

22.000 1125 251 502 19] 255 196 261 201 269
-78 -61

24.000 1050 234 468 182 249 187 257 19] 263
-86 -66

26.000 975 219 438 172 245 177 253 182 260
-99 -73

29.000 740 180 360 145 216 151 227 157 237
-107 -77

31.000 600 155 310 - -

126 197 137 2i4

I
 ECONOMY CRUISE POWER • 2000 RPM • ISA -20°C
Pressure Torque Fuel 1-o,, Total Airspeed -

KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
.
Sea Level 28 -

2 1628 387 774 246 237 246 237 246 237

2000 21 -

6 1628 381 762 246 245 246 245 246 245

-10

4000 14 1628 376 752 246 252 246 252 246 252
-15

6000 6 1628 372 744 246 259 246 259 246 259
-19

8000 -

2 1628 368 736 246 267 246 267 246 267

-23

10.000 -

9 1560 349 698 238 267 241 270 244 274

-27

12.000 -I7 1470 328 656 229 265 233 269 236 273
-24 -31

14,000 1385 308 616 22! 263 224 268 228 271
-31 -35

16.000 1300 290 580 211 260 215 265 219 269
-38 -39

18.000 1225 272 544 202 257 207 263 2!! 268
-45 -43

20.000 I 150 256 512 194 255 198 261 202 267
-53

22.000 -47

1075 240 480 184 250 189 257 195 264

-60 -5]

24,000 1005 225 450 175 247 181 254 186 261
-69 -56

26.000 935 211 422 166 241 172 250 177 258
-81 -63

29.000 800 190 380 146 226 154 237 160 246
-89 -67

31.000 680 165 330 120 191 134 213 145 230
 ECONOMY CRUISE POWER • 2000 RPM • ISA -10°C > q
Pressure Torque Fuel Flow Total Airspeed -
KTS
Altitude IO/ T Per Engine Per Engine Fuel Flow 900( Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level 45 7 I628 38I 762 246 24I 246 241 246 241

2000 37 3 1628 375 750 246 248 246 248 246 248

4000 30 -

I 1628 370 740 246 256 246 256 246 256

6000 23 -

5 1628 366 732 246 264 246 264 246 264

8000 16 -

9 1555 350 700 239 264 24l 268 244 270

-13

10,000 9 1470 331 662 23\ 264 234 268 236 270
-17

12,000 I 1375 312 624 221 261 225 265 228 268
-21

14.000 -

6 1295 293 586 212 258 216 262 220 267

-13 -25

16,000 1220 275 550 203 255 208 26! 21I 265
-20

18,000 -29 1145 258 516 195 253 199 258 203 263
-34

20.000 -29 1080 242 484 186 249 191 256 194 261
-36 -38

-
22.000 1010 228 456 176 245 182 254 187 260
-44 -42

24.000 950 213 426 168 241 174 250 179 257
-51 -46

26,000 885 199 398 159 236 165 246 170 254
-63 -53

29.000 800 181 362 144 227 152 239 158 248
-69 -57

31.000 705 170 340 135 220 142 232 149 243 2
 ECONOMY CRUISE POWER • 2000 RPM • ISA
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude lO/.T Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb. 2
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level 63 I7 1628 377 754 246 246 246 246 246 246

2000 55 13 1628 372 744 246 253 246 253 246 253
4000 48 9 I590 363 726 245 261 246 26I 246 26I
.
6000 4\ 5 1515 346 692 237 26] 241 263 243 266

8000 34 I 1444 328 656 230 260 234 263 236 266

10.000 27 -

3 1365 311 622 221 258 225 262 228 265 .g

12.000 19 -

7 1285 292 584 213 255 216 260 220 264

-11

14.000 12 1215 275 550 204 254 208 258 2l2 263
-15

16.000 5 1140 259 518 195 250 200 255 204 261
-19

18.000 -

2 1055 243 486 187 248 19] 253 195 259

-11 -24

20.000 1015 230 460 178 244 183 250 188 257
-18 -28

22,000 950 215 430 169 240 175 248 180 255
-26 -32

24.000 890 202 404 160 235 167 245 172 252
-33 -36

26,000 830 189 378 15I 229 157 239 163 248
-44 -42

29,000 755 171 342 135 216 144 231 15! 242
-53 -47

31,000 690 158 316 120 200 132 220 141 234
 ECONOMY CRUISE POWER • 2000 RPM • ISA +10°C
Pressure Torque Fuel Flow Total Airspeed -
KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb. ...

Ft. °F °C Lb. Ft. Lb.. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level SI 27 1575 369 738 246 250 246 250 246 250

2000 73 23 1520 356 7\2 245 256 246 257 246 257
4000 66 19 1465 341 682 235 254 239 258 242 261

6000 59 15 1400 325 650 228 254 232 258 235 261

8000 52 11 1330 309 618 22\ 254 224 258 228 261
10.000 45 7 1260 292 584 212 251 216 256 220 260

12.000 37 3 !!90 276 552 203 248 208 255 212 259

14.000 30 -

1 I130 259 518 195 247 200 253 204 258

16.000 21 -

6 1065 244 488 187 244 192 25 \ 196 257

-10

18,000 14 10\0 230 460 178 24] 183 248 188 256
-14

20.000 7 945 216 432 169 237 175 246 181 253
-18

22.000 0 890 203 406 161 233 167 242 172 249
-22

24,000 -

8 840 190 380 152 228 159 239 165 247 -

-15 -26

26.000 785 178 356 143 22I 150 235 157 243
-27 -33

29.000 710 162 324 122 200 135 221 143 235
-35 -37

3L000 650 150 300 -

122 206 135 228

-
 ECONOMY CRUISE POWER • 2000 RPM •
ISA +20°C
Pressure Torque Fuel Flow Total Airspeed -
KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 900( Lb. 800C Lb. 7000 Lb. 2
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
o Sea Level 99 37 1425 347 694 237 246 240 248 242 25 ]

2000 91 33 1385 333 666 232 247 235 250 238 254

4000 84 29 1335 318 636 225 247 228 250 231 254

6000 77 25 1285 303 606 218 247 221 250 224 254

8000 70 21 1225 287 574 211 247 215 250 217 254

10,000 63 17 !!60 272 544 203 245 207 249 210 253 .g

12.000 55 13 I100 257 514 195 242 199 248 203 253

14.000 48 9 1040 242 484 186 239 19] 246 195 251

16.000 4\ 5 980 228 456 177 235 182 242 188 249

18.000 32 0 930 215 430 168 232 175 240 180 248

20.000 25 -

4 875 202 404 161 228 167 237 172 245

22.000 18 -

8 820 190 380 152 224 159 235 164 242

-13

24.000 9 775 178 356 143 220 15] 23I 156 240
-17

26.000 I 730 167 334 131 209 142 225 148 235
-23

29.000 -

9 655 150 300 - -

125 209 136 228
31 000 FOR VALUEd ABOVE 29.000 FT. REFER TO MAXIMUM CRUISE TABLES· 2
 ECONOMY CRUISE POWER • 2000 RPM • ISA +30°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude 104T Per Engine Per Engine Fuel Flow 900) Lb. 8000 Lb. 7000 Lb,
Ft. °F °C Lb. Ft. Lb. Hr. Lb.. Hr. CAS TAS CAS TAS CAS TAS
Sea Level 117 47 1285 326 652 226 235 229 239 232 24l

2000 109 43 1245 313 626 220 238 223 24\ 227 245

4000 102 39 12\5 299 598 215 239 218 242 22] 246
6000 95 35 1175 284 568 208 240 213 244 216 248

8000 88 31 1120 269 538 202 239 206 244 210 248

10.000 81 27 1065 256 512 194 238 198 243 202 248

12.000 73 23 1010 240 480 185 235 190 241 195 247
-
14.000 66 19 960 225 450 176 231 182 239 187 245

16.000 57 14 900 210 420 168 228 174 235 179 242

18.000 50 10 850 197 394 259 223 165 232 171 240

20.000 43 6 795 184 368 150 219 156 228 162 236
22,000 36 2 740 171 342 140 21I 148 222 155 233

24.000 28 -

2 690 158 316 126 196 138 215 146 228

26.000 19 -

7 640 146 292 127 205 137 222

- -

31,000 FOR VALUES ABOVE 26.000 FT. REFER TO MAXIMUM CREISE TABLES.
 ECONOMY CRUISE POWER • 2000 RPM • ISA +37°C
Pressure Torque Fuel Flow Total Airspeed -
KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 700( Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level 128 53 I180 312 624 2l8 228 22] 232 25 235
2000 120 49 l l55 299 598 212 230 215 235 219 238
4000 113 45 1120 286 572 206 23] 210 236 214 240
6000 106 4l 1090 273 546 200 232 204 237 208 242
8000 99 37 1050 260 520 193 232 198 238 202 244
10.000 91 33 1005 244 488 186 231 191 237 195 243
12.000 84 29 950 228 456 178 228 183 235 188 242
14.000 77 25 900 214 428 169 226 175 233 181 241
16.000 70 21 840 200 400 f61 221 167 228 173 237
18.000 63 17 785 186 372 151 215 158 224 164 2.33
20.000 54 12 735 173 346 141 207 149 220 155 228
22,000 46 8 670 160 320 126 192 138 210 146 222
24.000 39 4 615 I47 294 - -

125 197 135 214

26.000 32 0 560 135 270 - - -
123 202 -

29.000 - -
-

3LOO0 FOR VALUES ABOVE 26.000 FT. REFER TO MAXIMUM CRUISE TABLES.
 ECONOMY CRUISE POWER •
1900 RPM • ISA -30°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 9000 Lb. 7000 Lb.
8000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level 9 113 1628 386 772 246 233 246 233 246 233
-17

2000 1 1628 38\ 762 246 241 246 241 246 24\
-21

4000 -

6 1628 376 752 246 248 246 246 248

248
-13 -25

6000 1628 370 740 246 255 246 255 246 255
-18 -28

8000 1628 365 730 241 257 244 260 246 262
-26 -32

10.000 1628 360 720 238 261 241 264 244 268
-3 -36

12,000 I l 570 34 I 682 23 I 26 i 234 265 237 268

-42 -4]

14.000 1475 321 642 222 260 226 264 229 268
-49 -45

e 16.000 1380 300 600 214 258 217 261 221 266
-56 -49

18.000 1295 280 560 204 255 208 260 213 264
-63 -53

20.000 1220 262 524 195 251 200 257 204 263
-71 -57

22.000 1130 244 488 185 247 190 254 195 259
-78 -61

24.000 1050 227 454 175 Ñ\ 181 248 l86 256

-86 -66

26.000 965 211 422 165 235 171 244 176 251
-99 -73

29.000 730 180 360 132 198 142 214 150 225
-107 -77

31,000 590 160 320 -- -

128 200
- -
 ECONOMY CRUISE POWER •
1900 RPM • ISA -20°C

Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 900E Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb.!Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level 28 -

2 I 628 382 764 246 237 246 237 246 237

2000 21 -

6 1628 375 750 246 245 246 245 246 245

-10

4000 14 1628 370 740 246 252 246 252 246 252
-15
.
6000 6 1628 365 730 24] 255 244 257 246 259
-19

8000 -

2 1628 360 720 239 259 24\ 262 244 265

-23

10.000 -

9 1605 347 694 235 263 237 266 24] 269

-17 -27

12.000 1505 326 652 225 260 228 264 23] 267
-24 -31

14.000 1415 305 610 216 258 220 262 223 266
-3] -35

16.000 1325 287 574 207 255 211 259 215 264
-38 -39

18.000 1245 268 536 197 25] 202 256 206 262
-45 -43

20.000 I 165 252 504 188 248 194 255 198 261
-53 -47

22.000 1085 235 470 180 245 185 252 189 258
-60 -51

24.000 1010 219 438 170 240 175 245 18] 255
-69 -56

26.000 935 204 408 160 233 166 241 17] 249
-81 -63

29.000 790 180 360 136 208 144 22] 153 236
-89 -67

31.000 665 I 168 336 i 14 182 130 207 139 222

 ECONOMY CRUISE POWER • 1900 RPM • ISA -10°C > q
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude / T Per Engine Per Engine Fuel Flow 900 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb.. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level 45 7 I628 376 752 246 24 I 246 24 I 246 24 I

2000 37 3 I628 370 740 246 248 246 248 246 248

4000 30 -I 1628 364 728 242 253 246 256 246 256
-5

6000 23 1628 358 716 240 257 242 261 245 263
-9

8000 16 1610 350 700 235 261 238 264 24l 267
-13

10.000 9 1525 33] 662 227 261 230 263 233 267
-17

12.000 I 1420 31I 622 217 256 22] 261 224 264
-6 -2\

14.000 1330 292 584 208 253 212 258 216 263
-13 -25

16.000 1255 273 546 199 25! 203 255 208 261
-20 -29

18.000 1170 256 512 190 248 195 252 200 260
-29 -34

20,000 1100 239 478 182 244 187 251 191 257
-36 -38

- 22.000 1030 225 450 172 239 178 248 183 255
-44 -42

24.000 960 209 418 163 235 169 244 175 252
-51 -46

26.000 890 194 388 154 228 160 238 166 247
-63 -53

29.000 800 180 360 137 215 146 229 153 240
-69 -57

31,000 700 170 340 122 199 132 215 140 230
 ECONOMY CRUISE POWER • 1900 RPM • ISA
Pressure Torque Fuel Flow Total Airspeed - KTS
og
Altitude 10/ T Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7004 Lb. 2
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level 63 17 1628 368 736 246 246 246 246 246 246

2000 55 13 1628 362 724 242 249 246 253 246 253
4000 48 9 1628 356 712 241 256 243 258 246 261

6000 41 5 1580 346 692 135 257 238 261 241 263

8000 34 1 1500 328 656 227 256 230 260 234 263
-3

10.000 27 1420 310 620 218 254 221 258 226 263
-7

12.000 19 1330 291 582 209 252 214 257 217 261
-11

14.000 12 1255 273 546 201 249 205 255 209 260
-l5

16.000 5 1175 257 514 192 247 196 252 201 258
-2

18.000 -I 1085 240 480 182 242 188 249 192 256
-11 -24

20,000 1040 227 454 174 239 180 247 184 253
-18 -28

22.000 975 212 424 165 235 171 243 176 250
-26 -32

24,000 905 198 396 155 228 162 239 168 248
-33 -36

26.000 840 185 370 147 223 154 234 160 243
-42
-44

29,000 760 170 340 128 205 139 223 147 235
-53 -47

31.000 .
690 160 320 - -
126 210 137 227
 ECONOMY CRUISE POWER • 1900 RPM • ISA +10°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 800( Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
Sea Level 8\ 27 1628 362 724 246 250 246 250 246 250

2000 73 23 1600 358 716 241 252 243 255 246 257

4000 66 19 1540 343 686 234 252 237 256 240 259

6000 59 15 1470 326 652 227 252 230 256 233 259

8000 52 11 1395 310 620 219 250 222 256 226 259

10,000 45 7 1315 292 584 209 248 214 254 217 257

12.000 37 3 1240 276 552 201 246 205 252 209 256

14,000 30 -I I175 258 516 193 244 197 250 202 256
-6

14,000 21 1110 243 486 184 241 189 248 194 255
-10

18.000 14 1045 228 456 175 238 l81 246 186 253
-14

20,000 7 970 214 428 167 235 l73 242 178 249
-18

22.000 0 910 201 402 157 229 163 238 169 245
-8 -22

24,000 860 187 374 148 223 155 234 161 242
-15 -26

26.000 795 175 350 137 214 146 227 153 238
-27 -33

29.000 7\5 L60 320 -

130 215 139 228
-
-37

194
-35

31.000 650 145 290 115 130 220

- -
 ECONOMY CRUISE POWER • 1900 RPM •
ISA +20°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude lOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb. 2
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
e Sea Level 99 37 1510 349 698 236 245 239 248 24l 250 2

2000 91 33 1460 335 670 230 245 234 248 236 252

4000 84 29 1410 319 638 224 246 228 249 230 253

6000 77 25 1355 304 608 217 246 221 249 223 253

8000 70 21 1290 288 576 209 245 213 248 215 252
10.000 63 17 1220 273 546 202 243 205 248 208 251 ...

12,000 55 13 1155 257 514 193 241 197 247 202 251

14.000 48 9 1090 242 484 184 237 189 244 194 249
16.000 41 5 1025 228 456 175 233 180 240 185 247

18.000 32 0 970 214 428 166 229 172 236 177 245
-4

20,000 25 910 20\ 402 157 226 163 234 169 242
-8

22.000 18 850 188 376 148 22] 155 230 16I 238
-13

24.000 9 800 176 352 139 214 148 227 154 235
-17

26.000 1 750 165 330 128 203 140 221 147 233
-9 -23

29.000 665 147 294 119 199 132 22I

- -
31.000 FOR VALUEE ABOVE 29.00·) FT. REFER 10 MAX MUM RUISE TABLE
 ECONOMY CRUISE POWER • 1900 RPM •ISA +30°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb., Hr. Lb.; Hr. CAS TAS CAS TAS CAS TAS
Sea Level 117 47 1370 330 660 226 235 229 239 232 24!

2000 109 43 1325 317 634 220 238 223 242 227 245
4000 102 39 1295 302 604 215 239 218 242 22l 246

6000 95 35 1245 287 574 208 239 212 243 215 248

8000 88 31 1190 272 544 200 237 204 242 208 247
. .
10,000 81 27 1130 258 516 192 236 196 242 201 247

12.000 73 23 1070 242 484 183 233 188 239 193 245
.
14,000 66 19 1015 227 454 175 229 180 237 185 243

16,000 57 14 950 211 422 166 226 172 234 177 241

18,000 50 10 895 198 396 157 221 163 230 169 238

20,000 43 6 835 184 368 148 217 155 226 161 235

22,000 36 2 775 171 342 138 209 146 22I 153 231
-2

24.000 28 720 157 314 123 194 136 214 144 226
-7

26.000 19 660 145 290 - -

124 200 135 218

31.000 FOR VALUES ABOVE 26.000 FT. REFER TO MAXIMUM CRCISE TABLES.
 ECONOMY CRUISE POWER • 1900 RPM •
ISA +37°C
Pressure Torque Fuel Flow Total Airspeed -

KTS
Altitude IOAT Per Engine Per Engine Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb. 2
Ft. °F °C Lb. Ft. Lb. Hr. Lb. Hr. CAS TAS CAS TAS CAS TAS
e Sea Level 128 53 1265 317 634 218 228 22] 232 225 235

2000 120 49 1240 304 608 212 230 215 234 219 238

4000 113 45 1200 290 580 206 231 210 236 214 240
6000 106 4l 1165 277 554 199 231 203 236 208 241
8000 99 37 1120 264 528 192 231 197 237 202 243
10.000 91 33 1070 247 494 185 230 190 236 195 242
12.000 84 29 1010 231 462 177 227 182 234 188 241
14.000 77 25 955 216 432 168 224 174 231 179 239

16.000 70 21 890 202 404 .!58 219 165 227 171 235
18.000 63 17 830 187 374 149 213 156 222 162 231
20.000 54 12 775 174 348 139 205 148 218 154 227
22.000 46 8 705 160 320 126 192 136 208 144 221
24.000 39 4 645 147 294 - -
123 195 134 212

26.000
- - -
29.000
-
31,000 FOR VALUES ABOVE 24.000 FT. REFER TO MAXIMUM CRUlSE TABLES.
 MAXIMUM RANGE POWER •
1900 RPM •
ISA -30°C
9000 Pounds 8000 Pounds 7000 Pou ids

Torque Fuel Torque Fuel Torque Fuel

Pressure Per Flow Airspeed Per Flow Airs Jeed Per Flow Airspeed
Altitude IOAT Engine Total KTS Engine Totai KS Engine Total KTS
Ft. °F °C Lb. Ft. Lb.. Hr. CAS TAS Lb. Ft. Lb. Hr. CAS TAS Lb. Ft. Lb. Hr. TAS
-13
CAS
Sea Level 9 760 478 175 166 690 454 169 160 600 424 165 156 2 m
-17

2000 I 740 458 171 168 670 436 165 161 580 406 160 157
-21
m
4000 -6 720 440 168 168 650 416 162 164 560 386 157 158
-13 -25

6000 710 424 163 169 640 402 158 165 550 368 154 158
-18 -28

8000 700 406 159 170 630 380 155 166 540 352 151 160
-26 -32

10.000 690 390 156 172 620 366 152 167 530 338 148 162
-33 -36

12.000 680 378 153 173 610 354 149 169 520 324 145 164
-42 -41

14,000 670 362 150 175 600 338 146 170 520 314 142 167
-49 -45 I
16.000 665 | 348 !47 177 600 326 142 172 520 304 141 169
-56 -49

18.000 660 336 143 177 600 314 139 173 520 294 139 173
-63 -53

20.000 655 324 141 181 600 304 135 175 520 282 136 175 y
-7\ -57

22.000 655 3\4 138 183 600 292 133 176 520 276 134 178
-78 -61

24.000 655 306 134 185 600 288 129 178 520 264 13\ 181
-86 -66

26,000 655 298 132 188 600 274 127 181 520 256 128 182
-99 -73

29.000 655 290 128 192 600 266 122 184 520 246 122 184 2
31,000 FOR VALUES ABOVE 29.000 FT. REFER TO MAXIMJM CRUISE TABLES.
yo MAXIMUM RANGE POWER •
1900 RPM • ISA -20°C om
9000 Pounds 8000 Pounds 7000 Pou ids

Torque Fuel Torque Fuel Torque Fuel

..
Pressure Per Flow Airspeed Per Flow Airspeed Per Flow Airs >eed
Altitude . Total
IO .T Engine KTS Engine Total KTS Engine Total KS
o Ft. °F °C Lb. Ft. Lb. Hr. CAS TAS Lb. Ft. Lb. Hr. CAS TAS Lb. Ft. Lb. Hr. CAS TAS
-2

Sea Level 28 770 482 175 169 700 458 169 163 610 428 165 159
-6

2000 21 750 462 17] 170 680 440 165 164 590 4l0 160 159
-10

4000 14 730 444 167 171 660 420 162 167 570 390 157 161
-15

6000 6 720 428 163 172 650 400 158 168 560 372 154 161
-2 -19

8000 710 410 159 174 640 384 155 168 550 356 154 164
-9 -23

10.000 700 394 156 175 630 370 152 170 540 342 148 165
-27

- --
12.000 -I7 690 382 153 176 620 358 149 173 530 328 145 168
-24 -3)

14.000 680 366 150 179 610 342 146 I74 520 312 142 168
-35

16,000 -3I 675 352 147 18! 605 328 142 175 520 302 139 17]
-39

18.000 -38 670 340 143 182 605 316 139 176 520 292 137 175 ..

-45 -43

20.000 665 328 140 184 605 306 135 178 520 280 134 177
-53 -47

22.000 665 318 137 187 605 294 133 181 520 274 132 180
-60 -5]

24.000 665 310 134 188 605 290 I29 182 520 262 129 182
-56

26.000 -69 665 302 13] 19I 605 276 12¯ 185 520 254 126 183
-81 -63

29.000 665 294 126 193 605 268 122 188 520 244 I2l 185 2
31.000 FOR VALUES ABOVE 29.000 FT. REFER TO MAXIM MC (UISE TABLES. m 2
 MAXIMUM RANGE POWER • 1900 RPM •
ISA -10°C
.. 9000 Pou ids 8000 Pour ds 7000 Pounds
Torque Fuel Torque Fuel Torque Fuel
Pressure Per Flow Airspeed Per Flow Airspeed Per Flow Airspeed
Altitude IOAT Engine Total KS Engine Total KTS Engine Total KTS
Ft. °F °C Lb. Ft. Lb. Hr. CAS TAS Lb. Ft. Lb.. Hr. CAS TAS Lb. Ft. Lb. Hr. CAS TAS
Sea Level 45 7 780 486 175 173 710 462 169 167 620 432 165 162

2000 37 3 760 466 171 173 690 444 165 167 600 414 160 162
-l

4000 30 740 448 167 174 670 424 162 169 580 394 157 164
-5

6000 23 730 432 163 175 660 410 158 170 570 376 154 165
-9

8000 16 720 414 159 177 650 388 155 172 560 360 15l 167
-13

10.000 9 7l0 398 156 179 640 374 152 174 550 346 l48 168
-17

12,000 I 700 386 153 180 630 362 149 176 540 332 145 17 \
-6 -21

14.000 690 370 150 182 620 346 146 177 530 316 142 172
-13 -25

16.000 685 356 147 185 615 332 142 179 525 302 139 175
-20 -29

18.000 680 344 143 186 615 320 139 181 520 290 135 176
-29 -34

20.000 675 332 140 188 6I5 310 135 182 520 278 133 178
-36 -38

22.000 675 322 137 190 6]$ 298 133 185 520 272 130 181
-44 -42

24,000 675 3I4 134 193 615 294 129 186 520 160 127 182
-5\ -46

26,000 675 306 130 194 615 280 127 188 520 252 l24 185
-53

29.000 -63 675 298 125 196 615 272 122 191 520 242 !!9 187

31.000 FOR VALUES ABOVE 29.000 FT. REFER TO MAX!MUM CRUISE TABLES.
 MAXIMUM RANGE POWER •
1900 RPM • ISA
9000 Pounds 8000 Pounds 7000 Pou ids -

Torque Fuel Torque Fuel Torque Fuel

Pressure Per Flow Airspeed Per Flow Airs >eed Per Flow Airs >eed
Altitude 10?T Engine Total KTS Engine Total KS Engine Total KS
Ft. °F °C Lb. Ft. Lb. Hr. CAS TAs Lb. Ft. Lb. Hr. CAS TAS Lb. Ft. Lb. Hr. CAS TAS
Sea Level 63 17 790 490 175 175 720 466 169 169 630 436 165 165
2000 55 13 770 470 171 176 700 448 165 170 610 418 160 166
4000 48 9 750 452 167 177 680 428 162 172 590 398 157 167
6000 41 5 740 436 163 179 670 410 158 174 575 380 154 168
8000 34 I 730 418 159 181 660 392 155 175 565 362 15] 170
-3

10.000 27 720 402 156 182 650 378 152 177 555 348 148 172
-7
-

12.000 19 710 390 153 184 640 366 149 179 545 334 145 174 %
14.000 12 -Il 700 374 150 186 630 350 146 181 540 320 142 175 -

-15

16.000 5 695 360 147 188 625 336 142 182 535 306 139 178
-2 -19

18.000 690 348 143 190 620 324 139 184 535 294 135 180 -

-11 -24

20.000 685 336 140 192 615 314 135 186 530 282 133 182
-18 -28

22.000 685 326 137 195 615 302 133 188 530 276 130 184
-26 -32

24.000 685 318 134 196 615 294 129 190 530 264 127 186
-33
-36

26.000 685 310 130 198 615 284 127 193 530 256 124 188
-44 -42

29.000 685 302 125 201 615 276 122 195 530 246 119 190 2 -

31,000 FOR VALUES ABOVE 29,000 FT. REFER

zo 2
TO MAXIMUM CAUISE TABLES. U
 MAXIMUM RANGE POWER • 1900 RPM • ISA +10°C
9000 Pou ids 8000 Pounds 7000 Poul ds
Torque Fuel Torque Fuel Torque Fuel
y Pressure Per Flow Airs »eed Per Flow Airspeed Per Flow Airs >eed
X Altitude lOAT Engine Total KS Engine Total KTS Engine Total IC'S
Ft. °F °C Lb. Ft. Lb.. Hr. CAS TAS Lb. Ft. Lb.. Hr. CAS TAS Lb. Ft. Lb.. Hr. CAS TAS
Sea Level 81 27 800 494 175 179 730 470 169 173 640 440 l65 168

2000 73 23 780 474 171 179 710 452 165 173 620 422 160 168

4000 66 19 760 456 167 180 690 432 162 175 600 402 f57 169

6000 59 15 750 440 163 182 680 414 158 176 590 384 154 171

8000 52 11 740 422 159 183 670 396 155 179 580 366 ISI 174

10.000 45 7 730 406 156 185 660 382 152 180 570 352 148 l75

12.000 37 3 720 394 153 187 650 370 149 183 560 338 145 177
-l

14,000 30 710 378 149 189 640 354 146 185 550 324 142 179
-6

16,000 21 705 364 146 191 635 340 142 187 545 310 139 182
-10

18.000 14 700 352 142 193 630 328 139 188 540 298 135 183
-14

20,000 7 695 340 139 195 625 318 135 189 540 286 132 185
-18

22.000 0 695 330 136 198 625 306 132 191 540 280 129 188
-8 -22

24,000 695 322 133 200 625 298 129 193 540 268 126 189
-15 -26

26.000 695 3\4 129 202 625 288 126 196 540 260 123 192
-27 -33

29,000 695 306 124 204 625 280 121 199 540 250 118 195 2
3L000 FOR VALUES /-ROVE 29.000 FT. REFER TO MAXIN UM CRUISE TABLES. Em
 IMUM RANGE POWER • 1900 RPM •
ISA +20°C
9000 Pou ids 8000 Pou ids 7000 Pounds
Torque Fuel Torque Fuel Torque Fuel
Pressure Per Flow Airspeed Per Flow Airspeed Per Flow Airspeed
Altitude lOAT Engine Total KTS Engine Total KTS Engine Total KTS
e Ft. °F °C Lb.Ft. Lb.Hr.CASTAS Lb.Ft. Lb.xHr.CASTAS Lb.Ft. Lb.Hr.,CASTAS
Sea Level 99 37 810 498 175 182 740 474 169 175 650 444 165 17]

2000 91 33 790 478 17l 182 720 456 165 175 630 426 160 I7]

4000 84 29 770 460 167 182 700 436 162 178 610 406 157 172

6000 77 25 760 444 163 185 690 4]8 158 180 600 388 154 174

8000 70 21 750 426 159 187 680 400 155 182 590 370 151 176

10,000 63 17 740 410 156 188 670 386 152 183 580 356 148 178
-
12.000 55 13 730 398 152 189 660 374 149 186 570 342 145 181

14.000 48 9 720 382 148 191 650 358 146 188 560 328 142 182

16.000 41 5 715 368 146 194 645 344 142 189 555 314 139 185

18.000 32 0 710 356 142 196 640 332 139 191 550 302 135 187
-4
.
.. 20.000 25 705 346 139 198 635 322 135 193 550 290 132 188
-8

22,000 18 705 334 136 202 635 310 132 195 550 284 129 191
CW + -13

*
oN 24.000 9 705 326 133 203 635 302 129 197 550 272 126 193
-17

26.000 1 705 318 129 204 635 292 126 200 550 260 123 195 < >
- - 29.000 FOR VALUES ABOVE 26.000 FT. REFER TO ECONOMY CRUISE POWER TABLES. 2 -

31.000
 MAXIMUM RANGE POWER•l900 RPM•ISA +30°C
9000 Pou ids 8000 Pour ds 7000 Pounds
Torque Fuel Torque Fuel Torque Fuel
Pressure Per Flow Airspeed Per Flow Airspeed Per Flow Airs seed
Altitude lOAT Engine Total KTS Engine Total KTS Engine Total KTS
Ft. °F °C Lb. Ft. Lb. Hr. CAS TAS Lb. Ft. Lb. Hr. CAS TAS Lb. Ft. Lb.. Hr. CAS TAS
Sea Level I 17 47 820 502 175 182 750 478 169 176 660 448 165 172 2
2000 109 43 800 482 17\ 185 730 460 165 179 640 430 160 174 M

4000 102 39 780 464 167 186 7\0 440 162 181 620 4l0 157 175

6000 95 35 770 448 163 188 700 422 158 182 610 392 154 176

8000 88 31 760 430 159 189 690 404 155 184 600 374 15] 179

10.000 81 27 750 4L4 156 192 680 390 152 187 590 360 148 182

12.000 73 23 740 402 152 193 670 378 149 189 580 346 145 184

14.000 66 19 730 386 148 195 660 362 146 191 570 332 142 186

16.000 57 14 725 372 146 197 655 348 142 193 565 3\8 139 188

18.000 50 10 720 360 142 199 650 336 139 195 560 306 135 190

20.000 43 6 715 350 139 202 645 326 135 197 560 294 132 192

22.000 36 2 715 • 338 136 205 645 314 132 199 560 288 129 195
-2

24,000 28 715 330 133 208 645 306 129 201 560 276 126 196

26.000 FOR VALUES ABOVE 24.000 FT. REFER FO ECONOMY CRUllE POWE I TABLES

29,000
 MAXIMUM RANGE POWER • 1900 RPM • ISA +37°C -
o
9000 Pounds 8000 Pounds 7000 Pounds
Torque Fuel Torque Fuel Torque Fuel
y Pressure Per Flow Airspeed Per Flow Airspeed Per Flow Airspeed
M Altitude lOAT Engine Total
X KTS Engine Total KTS Engine Total KTS
e g Ft. °F °C Lb. Ft. Lb. Hr. CAS TAS Lb. Ft. Lb. Hr. CAS TAs Lb. Ft. Lb. Hr. CAS TAS 2
Sea Level 128 53 825 504 175 182 755 480 169 177 665 450 165 173

2000 120 49 805 484 170 185 735 462 165 180 645 432 160 175

4000 113 45 785 466 167 188 715 442 162 182 625 412 157 176
2
6000 106 41 775 450 163 190 705 424 158 185 615 394 154 179

8000 99 37 765 432 159 193 695 406 155 188 605 376 151 182

10.000 91 33 755 416 156 195 685 392 152 188 595 362 148 183
- -
12.000 84 29 745 404 152 195 675 380 149 192 585 348 145 186
14.000 77 25 735 388 148 198 665 364 146 195 575 334 142 188 .

16.000 70 21 730 374 145 199 660 350 142 195 570 320 139 190

18.000 63 17 725 362 142 202 655 339 139 197 565 308 135 193 ..

20.000 54 12 725 352 137 202 650 328 134 198 560 296 132 195

24.000 FOR VALUES ABOVE 20.000 FT. REFER TO ECONOMY CRUlSE POWER TABLES
26.000

29.000 2 -

31.000
zo 2
m
 SINGLE ENGINE CRUISE POWER
2000 RPM • ISA -30°C
Pressure Airspeed -

KTS
Altitude IOAT Torque Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. CAS TAS CAS TAS CAS TAS
-26 -32

10,000 1628 374 175 192 177 195 180 197

-33 -36

12.000 1610 364 17\ 194 174 196 176 200

-42 -41

14.000 1500 345 162 189 166 194 169 198

-49 -45

16.000 1400 32\ 153 184 158 189 16] 195

-56 -49

18.000 1290 299 142 177 148 183 154 191

-63 -53

20.000 1185 280 129 167 136 175 145 187

 SINGLE ENGINE CRUISE POWER
2000 RPM • ISA -20°C
Pressure Airspeed -

KTS
Altitude lOAT Torque Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. CAS TAS CAS TAS CAS TAS
-9 -23

10.000 1628 374 173 194 175 196 178 200

-17 -27

12.000 1525 350 165 190 168 194 171 197

-24. -3]

14.000 1430 328 156 187 160 191 165 195

-31 -35

16.000 1340 306 148 182 152 188 157 194

-38 -39
•
© 18.000 1235 285 135 172 142 181 149 190
-45 -43

y 1 20.000 I 135 264 - -

129 170 140 184 ...
 SINGLE ENGINE CRUISE POWER
2000 RPM • ISA -10°C
Pressure Airspeed -

KTS
Altitude lOAT Torque Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb.. Ft. Lb. Hr. CAS TAS CAS TAS CAS TAS
-13

10.000 9 1555 356 168 192 170 195 174 199

-17

12.000 L 1450 332 158 188 162 191 166 195

-6 -21

14.000 1360 310 150 182 154 188 158 194

-13 -25

16.000 1270 290 140 [76 145 182 152 191

-20 -29

18.000 1175 272 127 165 134 175 143 186

-29 -34

20,000 1070 250 - 122 165 134 180

-
 SINGLE ENGINE CRUISE POWER
2000 RPM • ISA
Pressure Airspeed -

KTS
Altitude IO/ T Torque Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Br, CAS TAS CAS TAS CAS TAS
-3

Y -
10.000 27 1460 340 160 187 164 191 168 195
-7

12.000 19 1375 314 152 182 156 188 160 193

-11

14.000 12 1280 297 142 176 148 182 154 190

-15

16.000 5 I l90 278 130 167 137 175 146 187

-2
-19

18.000 1I10 260 -

125 166 137 182
-
-11 -24

20.000 1000 236 -

126 173 .
- -
 SINGLE ENGINE CRUISE POWER
2000 RPM • ISA +10°C
Pressure Airspeed - KTS
Altitude IOAT Torque Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. CAS TAS CAS TAS CAS TAS

10,000 45 7 1375 323 154 182 157 186 16.1 191

12,000 37 3 1285 301 144 176 149 183 154 189

14.000 30 -I 1205 283 134 169 140 177 148 187

i
-6

N 16,000 2\ !!20 265 118 154 128 167 139 182

-10

18.000 14 1040 247 -

- - -

131 177
-l4

20.000 7 945 226 -

- -

I19 167
-
 SINGLE ENGINE CRUISE POWER
+20°
2000 RPM • ISA C
Pressure Airspeed -

KTS
Altitude IOAT Torque Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. CAS TAS CAS TAS CAS TAS

10.000 63 17 1280 307 145 175 150 181 155 188

12.000 55 13 1200 288 134 168 14] 175 148 185

<
m 14.000 48 9 1125 270 122 157 131 168 141 181

16.000 41 5 1045 252 - -

121 160 132 176

18.000 32 0 970 234 - - -

123 169

20.000
 SINGLE ENGINE CRUISE POWER
2000 RPM •
ISA +30°C 2

Pressure Airspeed -

KTS
Altitude lOAT Torque Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. FT. Lb. Hr. CAS TAS CAS TAS CAS TAS

cm 10,000 81 27 1190 291 135 166 142 174 148 182

Ro
L2.000 73 23 1120 275 124 157 132 168 142 180 o2
14.000 66 19 1040 260 - -
121 158 134 175

16.000 57 14 955 240 - - -

123 168
-

18.000

20.000
 SINGLE ENGINE CRUISE POWER
2000 RPM • ISA +37°C

Pressure Airspeed -

KTS
Altitude 10AT Torque Fuel Flow 9000 Lb. 8000 Lb. 7000 Lb.
Ft. °F °C Lb. Ft. Lb. Hr. CAS TAS CAS TAS CAS TAS
.
10,000 91 33 !!30 280 128 158 135 168 144 179
Oc

a Q 12.000 84 29 1060 267 - -

124 158 136 175

-
14.000 77 25 980 254 -
- - -
I27 |69

I6.000

I8.000

20.ooo
 SPECIFIC RANGE >
o
MAXIMUM CRUISE POWER 2000 RPM 8000 LBS. No

Pressure SPEClFlC RANGE -

NAU. Ml. LB.

Altitude yB
Ft. ISA -30°C ISA -20°C ISA -IO°C [SA ISA +l0°C ISA +20°C ISA +30°C ISA +37°C U

0
2000
4000
6000

a 8000 .374 .380 .383 .385 .405 .4f9 .435 .447

10.000 -

2
.383 .388 .393 .408 .427 .443 .459 .47

12.000 .394
I
,401 .413 .433 .451 .467

14.000
.483

.496
.410 .422 .436 .456 .476 .49] .508 .52]

16.000
.437 .447 .463 .481 .500 .518 .538 .546

18.000
.459 .473 .49 .508 .528 .544 .565 .575

20.000 .49] .502 .523

I .536 .551 .572 .596 .609

22.000
.525 .532 .554 .565 .58 .596 .624 .638

24.000 .557
I m
.569 .575 .592 .608 .629 .648 .659

26.000 .599 .609 .621 .638 .659

29,000
.660 .674

.624 .628 .643 .678 .680 .670

31.000
.666

on-
 SPECIFIC RANGE 2

2 o MAXIMUM CRUISE POWER 1900 RPM 8000 LBS.

Pressure SPECIFIC RANGE -

NAU. MI. LB.

Altitude
Ft. ISA -30°C ISA -20°C ISA -l0°C ISA ISA +l0°C ISA +20°C ISA +30°C ISA +37°C

0
2000
4000
6000

.377 .376 .376 .375 .402 .408 .429 .442

10.000 .383 .388 .425

.386 .440 .452

12.000 .394 .410

.403
.429 .447
465
.395 .461 .478 .488

14,000
.408 .422 .433 .453 .473 .487 .502 .512

16.000 .438 .448 .479 .532

.464 .496 .5 .537

18.000 .459 .475 .491 .508 .524

I2
.536 .561 .566

20.000 .491 .500 .520 .538 .549 .566 .592 .601

22.000
.524 .530 .553 .564 .578 .590 .612 .625

24.000 .560 .570 .575 .597 .603 .624 .633 .640

26.000 .587 .602 .611 .642 .646 .656 .649

29.000 .606 .624 .666 .673 .649 .629

-

31.000 .589 -
 SPECIFIC RANGE
ECONOMY CRUISE POWER 2000 RPM 8000 LBS.
Pressure SPECIFIC RANGE -

NAU. Ml./LB.
Altitude 2 1
Ft. ISA -30°C lSA -20°C ISA -10°C ISA lSA +10°C ISA +20°C lSA +30°C ISA +37°C E
.298 .306 .316 .326 .339 .357 .367 .372

0 .313 .321 .331 .340 .361 .375 .385 .393

2000 .326 .335 .346 .360 .378 .393 .405 .413

4000 .340 .361

.

.434
.348 .380 .397 .413 .430

6000
.352 .362 .383 .401 .417 .436 .454 .458

8000 .368 .405

.378 .421 .438 .458 .475 .486

10.000 .389 .425 .445 .462 .482 .502 .515

12,000 .4IO .447

.414 .435 .469 .488 .508 .531 .544

14.000
.439 .457 .475 .492 .514 .531 .560 .570

16.000 .461 .483 .500 .521 .539 .558 .589 .602

18.000 .493 .510 .529 .543 .569 .587 .620 .636

20.000 .520 .535 .557 .577 .596 .618 .649 .656

22.000
.564 .587 .606 .624 .649 .680
.549 .670

24.000 N
.578 .592 .618 .632 .660 .674 .702

26.000 .630 .623 .660 .675 .682 .647

-

29.000 .635 .645 .682 .696 .686

-

31.000 -
. - -

-·J © I E Un
 SPECIFIC RANGE
ECONOMY CRUISE POWER 1900 RPM 8000 LBS.
Pressure SPECIFIC RANGE -

NAU. MI. LB.

Altitude
Ft. ISA -30°C ISA -20°C ISA -10°C ISA ISA +l0°C ISA +20°C ISA +30°C ISA +37°C
.302 .310 .320 .334 .345 .355 .362 .366

0 .327 .349 .356 .385

.316 .335 .370 .382

2000 .330 .341 .351 .362 .373 .390 .407

.401

4000 .345 .352 .365 .377 .426

.393 .423

6000 .4IO
.356 .364 .377 .396 .431 .445 .449

8000 .383
.4I3
.367 .397 .416 .435 .454 .469 .478

10.000 .389 .405 .420 .442 .456 .481 .494 .506

12,000
.41 .430 .438 .467 .484 .504 .522 .535

14.000 I
.435 .451 .467 .490 .510 .526 .555 .562

16,000 .464 .478 .492 .519 .539 .595

18,000 .490 .506 .525 .544

.55I .58I
.565 .582 .614 .626

20,000 .521 .536 .573 .592 .612 .650

.646

22,000 .55I
.546 .559 .584 .604 .627 .645 .682

24.000 .578 .591 .613

.632 .649 .670 .690

26,000 .587 .614 .634 .656 .672 .677

29.000 .594 .6l7 .639 .656 .668

-

31.000 -
 SPECIFIC RANGE
MAXIMUM RANGE POWER 1900 RPM 8000 LBS.
Pressure SPEClFlC RANGE --

NAU. MI. LB
Altitude -

Ft. ISA -30°C ISA -20°C ISA -10°C ISA ISA +10°C ISA +20°C lSA +30°C ISA +37°C
.369 .369 .369
.352 .356 .363 .368
.361

0 .369 .373 .379 .383 .384 .389 .390

.376

2000 .402 .405 .408 .41 .412

.394 .398 .399

4000 .431
I .436
.410 .424 .425 .431
.414 .415

-
g 6000
.452 .455 .458 .463
.437 .438 .443 .446

d , M 8000 .456 .459 .465 .468 .471 .474 .478 .480

10.000 .477 .483 .486

.489 .495 .497 .500 .505

12.000 .503 .509 .512 .517 .523 .525 .528 .536

-
14.000
.542 .550 .549 .555 .557
.528 .534 .539

16.000 .551 .557 .566

.568 .573 .575 .580 .574

18.000 .576 .582 .587

.592 .594 .599 .604 .604

20.000 .603 .616 .621 .623 .624 .629 .634

22.000 -

.648 .652 .657

.618 .628 .633 .646

24.000
-

.678 .681 .685

.661 .667 .671

26.000 - -

29.000 - - - -
- -

3I.000 - - - - - -
SECTION 5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

THIS PAGE INTENTlONALLY LEFT BLANK

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-90
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

PA-31T
SPEED Vs. ÄLTITUDE
MAXIMUM TAKE-O WE GHT 9000 LBS.
Ilo

31000
30000

20000

20000

sooo

DFT

E000

0 r.
2(† H( N) itt ;‡i
11 UE AIRS =EED -

KlS.

SPEED VS. ALTITUDE

Figure 5-153

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

5-91
SECTION5 PIPER AIRCRAFT CORPORATION
PERFORMANCE PA-31T, CHEYENNE

PA-31 T
‡‡‡‡‡‡ ‡‡‡‡M‡‡‡W‡‡‡‡‡¾‡N‡‡‡‡‡‡‡
44XII - 41 OPERATING SPEIA

31000
30000

26000

20000

1800

0000

6000

0
1 0 230 250
DICATED AIRSPEED -

KTS.

MAXIMUM OPERATING SPEED

Figure 5-155

REPORT: 2210 ISSUED: SEPTEMBER 14, 1979

5-92
PIPER AIRCRAFT CORPORATION SECTION 5
PA-31T, CHEYENNE PERFORMANCE

PA-31T
41‡‡¾#‡ii‡‡#‡‡t#t‡M‡W‡###¾##4‡#4‡tttittill
SINGLE ENGINE SERVICE CEILING
4SSOCIATED CONDITIONS:
MI XIMUM CONTINUOUS POWER
MEAR RETRACTED, FLAPS 0°
INOb HRATIVE PROPELLER FEATH2 RED
OIL OOLER DOORS CLOSED EXT EPT
4 lEN OA DS ISA +23 :

NOTE
El VIC i IIUNG 15 THE PRES-
U .E 4 T!f IDE WHERE AIRPLANE
A (&PFiIUTYOFCLIMSINGBO
T .Ur . + ITH ONE PROPELLER
!?¾EE .

30000

25000

20000

isooo

loooo

sooo

O -40
-
à -R * 2D *
t I(

OUTSIDE AIR TEMP. -°C

SINGLE-ENGINE SERVICE CEILING

Figure 5-157

ISSUED: SEPTEMBER 14, 1979 REPORT: 2210

REVISED: AUGUST 28, 1980 5-93
 PA-31T
ENDURANCE PROFILE
31000 STANDARD DAY
3oooo
ÏÑ!ÍlAL FUELLOADING 366 U.S. GAL (2452 LBS.)
PROPELLER SPEED:
2000 RPM (MAXIMUM OR ECONOMY)
(CRuiSE POWER)
1900 RPM (MAXIMUM RANGE POWER)
asooo

15000

NOTE
ENDURANCE INCLUDES START,
TAXI. CLIMB. AND DESCENT wiTH
10000 45 MINUTES RESERVE AT MAxi-
MUM HANGE POWER

5000

o12aaseya
ENDURANCE HOURS
 PA-31T
RANGE PROFILE
STANDARD DAY
aoooo
ASSOCIATED CONDITIONS:
WEIGHT 9050 LBS. BEFORE ENG. START
FUEL AVIATION KEROSENE
FUEL DENSITY 6.7 LBS./GAL
25000
INITIAL FUEL LOADING 366 U.S. GALS. (2452 LBS.)
PROPELLER SPEED
(MAXIMUM CRUISE POWER) 2000 RPM
(MAXIMUM RANGE POWER) 1900 RPM
2oooo (ECONOMY CRUISE POWER) 2000 RPM

15000

NOTE
RANGE INCLUDES START. TAXI,
10000 CUMB AND DESCENT WITH 45
MINUTES RESERVE FUEL AT MAXI-
MUM RANGE POWER.

5000

900 1000 1100 1200 1300 1400 1500 1600

600 700 800
RANGE -

NAUTICAL MILES (ZERO WIND)

 Examples:
PA-31T , 2© 2
1 Fuel available for holding: 1200 lba
HOLDING TIME
700ÑLBS.
Pressure altitude: 20,000 ft.
Holding time: 4.1 hrs
1900 RPM
ISA
2 Required holding time: 1 hr.
Pressure altitude: 5,000 ft.
Fuel required: 360 lbs.

--i

TT2 PRESS ALT. -

FT.
31.000 RECOMMENDED HOLDING POWER
ALTUDE (FT.) TOROUBE20LB.FT.)
25,000
20,000 5,ooo 53o
16:000 10,000 540
10,000 15.000 550
5,000 20,000 560
SEA LEVEL 25,000 570
at,ooo soo

400 soo 12oo leoo 2000

FUEL REQUIRED -

LBS.
 Examples:available
PA-31T
for holding: 1200 lbs. HOLDIÑG TIME
Pressure altitude: 20.000 ft 9000 LBS.
Holding time: 3.6 hrs. 1900 RPM
ISA
2 Required holding time: 1 hr
Pressure altitude: 5,000 ft.
Fuel required: 400 lbs.

RECOMMENDED HOLDING POWER

ALTITUDE (FT.) TOROUE (LB. FT.)
..
S.L. 600

oc 8 10,000 620
1s.ooo eso
T -
PT
ao.ooo see
as,ooo eso
26.000 31,000 676
'
6 20,000
15.000
10.000
s,ooo
SEA LEVEL

0
400 800 12 0 1600 2000
FUEL REQUIREMENTS -

LBS.
 Wind: zero
Example: 16 min. 2 min. 14 min
Time to descend: - =

Cruise pressure altitude: 16,000 ft 135 lbs

Fuel to descend: 155 lbs. 20 lbs.
- =

Destination pressure altitude: 2,000 ft

Weight all PA-31T Distance to descend: 66 n.m. 9 n.m = 57 naut. miles
-

TIME, FUEL AND DISTANCE TO DESCEN

1000 FPM RATE OF DESCENT
al.ooo
so.coa

25,000 DESCEND AT VMO FROM 31,000 FT. TO

18.000 FT. THEN 214 KIAS TO BEA LEVEL
. POWER SHOULD BE MONITORED TO
MAINTAIN SPEED AND HATE OF DES-
.. CENT. DISTANCES SHOWN ARE FOR
u. ZERO WIND. THIS INFORMATIOM MAY BE
USED FOR ALL AINCRAFT WEIGHTS.
2cooo

CRUISE
is.ooo

DESTINATION

O
O 10 20 30 0 100 200 300 0 40 90 120 160 ..

TIME TO DESCEND FUEL TO DESCEND -

LBS. DISTANCE TO DESCEND

MINUTES NAUTICAL MILES (ZERO WIND)
TT PA-31T :i
BALKED LANDING CLIMB
Example: ASSOCIATED CONDITIONS:
OAT: +io°C MAXIMUM CONTINUOUS POWER
Pressure altitude: 2000 ft. GEAR EXTENDED, FLAPS 40°
Weight: 8500 lbs. OIL COOLER DOORS CLOSED
CLIMB SPEED 99 KIAS
Rate of climb: 1760 F.P.M.
2500

00 2000

i ••• 15 0 0

ISA
1000 \

BOO

-30

O 10 0 TO 20 30 40 50 9000 8500 8000 750 7000

ouTsioE AIR TEMP. -

°C WEIGHT -
LBS
 Example
oxr o•c
BALKED LANDING CLIMB
eo
sÊiÎs
climy; 455 FPM
(SAS OVERRIDE ON)
400 SHP LIMIT
700
GEAR EXTENDED, FLAPS 40°
OIL COOLER DOORS CLOSED •

CLIMB SPEED 109 KIAS

600

300

ISA

200 HC

-30 -20 -10

0 10 20 30 40 50 9000 8000 7000

OUTSIDE AIR TEMP. -

°C WEIGHT -
LBS.
"*
m'e"
PA-31T :2
LANDING DISTANCE OVER 50 FT. 9|
© ASSOCIATED CONDITIONS:
PAVED, LEVEL, DRY RUNWAY, FLAP SETTING 40°
gg
APPROACH AT 98 KIAS < W
BRAKING HEAVY IN ROLL-OUT M >
Example 2
WITHOUTPROPELLER REVERSlNG
OAT: 10°C ANTI-ICE OPF 2
Pressure altitude: 2000 ft 3100 N
Weight: 8600 lbs
Wind: 10 knots
Ground roll: 1260 ft
Total distance: 2270 ft 2600 .

60
1600

ISA

-30 -20
soo
-10

0 10 20 30 40 60 9000 8000 7000 0 10 20 30 0 50

OUTSIDE AIR TEMP. -

*C WEIGHT -
LBS. WIND COMPONENT BARRIER -

FT.
-

KTS.
a;; PA-31T "2
LANDING DISTANCE OVER 50 FT.
ASSOCIATED CONDITIONSi
PAVED, LEVEL, DRY RUNWAY FLAP SETTING 40
APPROACli AT 98 KIAS
HEAVY BRAKING IN ROLL-OUT
Example: WITH PROPELLER REVERSING
GAT 10°C
ANTI-ICE OFF
Pressure altitude: 2000 ft 2900
Weight: 8600 lbs.
Wind: 10 knots
Ground roll: 1000 ft
Total distance: 1900 ft 2400

.
1900

ISA

.. -20 -10
400
30 0 10 20 30 40 50 9000 8000 7000 0 10 20 30 0 50
OUTSIDE AIR TEMP. -

C WEIGHT -

LBS. WIND COMPONENTS BARRIER

KTS.
- -

FT.
 PA-31T 4ooo
LANDING DISTANCE OVER 50 FT.
Example: ASSOCIATED CONDITIONS:
OAT: 10°C PAVED, LEVEL, DRY RUNWAY ..

Pressure altitude: 2000 ft SAS INOPERATIVE, FLAPS 40. e asco

Weight: 8600 lbs. APPROACH AT 109 KIAS
Wind: 10 knots BRAKING HEAVY IN ROLL-OUT
Ground roll: 1250 ft. WITHOUT PROPELLER REVERSING
Total distance: 2830 ft ANTI-ICE OFF 3000

1500

-30 -10 500

0 30
-20

0 10 20 30 40 ED 9000 8000 7000 10 20 0 50

OUTSIDE AIR TEMP. -

°C WEIGHT -

LBS. BARRIER -

FT.
WIND COMPONENT -

KTS.
 PA-31T
SHORT FIELD LANDING DISTANCE
o OVER 50 FT.
Example: ASSOCIATED CONDITIONS:
OAT: 10 C PAVED, LEVEL, DRY RUNWAY
Pressure altitude: 2000 ft. FLAP SETTING 40° gr
Weight: 8600 lbs APPRÔACH 91 KIAS
Wind: 10 knots HEAVY BRAKINGIN ROLL-OUT 2500
Ground roit: 840 ft. WITH PROPELLER REVERSING
ANTI-ICE OFF
Totaldistance: 1740 ft

: 2000

1500 - ,

00 1000

t isA

soo

-30
-20 -10

0 to 20 30 40 50 9000 8000 7000 0 10 20 30 0 50 o

OUTSIDE AIR TEMP. -*C WEIGHT -

LBS. WIND COMPONENT BARRIER -

FT.
-

KTS.