Piper CHEROKEE WARRIOR 1976 Owner's manual

Table of Contents
SECTION 1
(Orange Tab)
SECTION
(Orange)
SECTION
(Orange)
SECTION
(Clear)
SECTION
(Clear)
SECTION
(Blue)
SECTION
(Yellow)
SECTION
(Yellow)
SECTION
(Yellow)
SECTION
(Yellow)
MISC.
(Red)
2
3
4
5
6
7
8
9
10
GENERAL
LIMITATIONS
EMERGENCY PROCEDURES
NORMAL PROCEDURES
PERFORMANCE
WEIGHT AND BALANCE
AIRPLANE AND ITS SYSTEMS
HANDLING, SERVICING, MAINTENANCE
SUPPLEMENTS
OPERATING TIPS
A.D.'s, AVIONICS INSTRUCTIONS

r
r
r
Piper Warrior
PA28-151
1976
N7963F

jj
PIPER CHEROKEE WARRIOR
FAA APPROVED IN NORMAL AND UTILITY
CATEGORIES BASED ON CAR 3 AND FAR PART 21,
SUBPART J THIS HANDBOOK INCLUDES THE
MATERIAL REQUIRED TO BE FURNISHED TO THE
PILOT BY CAR 3 AND FAR PART 21, SUBPART J
AND CONSTITUTES THE APPROVED AIRPLANE
FLIGHT MANUAL AND MUST BE CARRIED IN THE
Al RPLANE AT ALL TIMES.
PA-28-151
REPORT: VB-780
FAA APPROVED BY:
WARD EVANS
D.O.A. NO. SO-1
PIPER Al RCRAFT CORPORATION
VERO BEACH, FLORIDA
AIRPLANE SERIAL NO.
28-7715251
AIRPLANE REGISTRATION NO. N7963F
DATE OF APPROVAL: JUNE 17,1976
HANDBOOK PART NO. 761 623

. ^- ■ • ^S^v
WARNING
EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS MANUAL TO
APPLICABLE AIRCRAFT. THIS MANUAL REVISED AS INDICATED BELOW OR
SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE
FACE OF THE TITLE PAGE WHEN OFFICIALLY APPROVED. SUBSEQUENT REVISIONS
SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED.
MODEL PA-28-151, CHEROKEE WARRIOR
PILOT'S OPERATING HANDBOOK, REPORT: VB-780 REVISION i
PIPER AIRCRAFT CORPORATION
APPROVAL SIGNATURE AND STAMP.
■'"**?r*!i
Published by
PUBLICATIONS DEPARTMENT
Piper Aircraft Corporation
Issued: June 17, 1976
"**i°Bs*\
REPORT: VB-780

APPLICABILITY
Application of this handbook is limited to the specific Piper PA-28-151 model airplane designated by
serial number and registration number on the face of the title page of this handbook.
This handbook cannot be used for operational purposes unless kept in a current status.
REVISIONS
The information compiled in the Pilot's Operating Handbook will be kept current by revisions
distributed to the airplane owners.
Revision material will consist of information necessary to update the text of the present handbook
and/or to add information to cover added airplane equipment.
I. Revisions
Revisions will be distributed whenever necessary as complete page replacements or additions and shall
be inserted into the handbook in accordance with the instructions given below:
1. Revision pages will replace only pages with the same page number.
2. Insert all additional pages in proper numerical order within each section.
jf»> 3. Page numbers followed by a small letter shall be inserted in direct sequence with the same
v . common numbered page.
r
II. Identification of Revised Material
Revised text and illustrations shall be indicated by a black vertical line along the outside margin of the
page, opposite revised, added or deleted material. A line along the outside margin of the page opposite the
page number will indicate that an entire page was added.
Black lines will indicate only current revisions with changes and additions to or deletions of existing
text and illustrations. Changes in capitalization, spelling, punctuation or the physical location of material
on a page will not be identified by symbols.
ORIGINAL PAGES ISSUED
The original pages issued for this handbook prior to revision are given below:
Title, ii through v, 1-1 through 1-14, 2-1 through 2-8, 3-1 through 3-12, 4-1 through 4-16, 5-1 through
5-24, 6-1 through 6-56, 7-1 through 7-24, 8-1 through 8-16, 9-1 through 9-10, 10-1 through 10-2.
REPORT: VB-780
iii

PILOTS OPERATING HANDBOOK LOG OF REVISIONS
Current Revisions to the PA-28-151 Cherokee Warrior Pilot's Operating Handbook, REPORT: VB-780
issued June 17, 1976.
Revision
Number and
Code
Rev. 1-761 623
(PR760803)
Rev. 2-761 623
(PR770118)
Rev. 3-761 623
(PR770223)
Revised
Pages
643
34
3-11
4-5
4-7
4-8
4-14
5-11
64
6-5
6-35
7-13
10-1
10-2
1-6
3-11
44
4-9
64
7-24
Description of Revision
Revised items 183, 185 and 187.
Revised Open Door procedure.
Revised para. 3.27 info.
Revised Takeoff procedure.
Added Caution to para. 4.9;.relocated material
to page 4-8.
Added relocated material from page 4-7.
Added Note to para. 4.31.
Removed "GEAR DOWN" from Fig. 5-1.
Added A & B values to Fig. 6-3.
Revised weight and balance formula.
Revised item 79 Arm and Moment.
Revised wording in text.
Revised 10.3 (c); relocated material to page 10-2.
Added relocated material from page 10-1.
Corrected to "Meteorological."
Revised NOTE.
Revised Starting Engine When Hot procedure.
Revised 4.13 (b).
Revised Leveling Diagram illustration.
Added ELT test info.
FAA Approval
Signature and
Date
Ward Evans
August 3, 1976
/ ) \ f
_ Ward Evans
Jan. 18, 1977
Ward Evans
Feb. 23, 1977
REPORT: VB-780
iv

PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont)
Revision
Number and
Code
Rev. 5-761 623
(PR790216)
(cont)
Revised
Pages
7-18
7-21
7-23
*
Rev. 6-761 623
(PR880817)
V
1-3
1-6
1-7
2-1
2-2
3-i
3-1
4-i
4-1
i 4-3,
4-4,
4-5
4-7
4-8
4-11
4-12
4-16
5-1
5-3,
5-4,
5-5,
5-6
6-1
6-3
6-6
6-7
6-9,
6-10
6-11
6-12
6-17
7-12
7-22
8-1
8-3
8-4
8-11
8-12
9-5
10-i
10-1
10-2
Description of Revision
Revised para. 7.21.
Added Caution to para. 7.23.
Revised para. 7.35.
Revised Table of Contents.
Revised para. 1.7.
Revised para. 1.19(b).
Revised para. 1.19(e).
Revised para. 2.1.
Revised para. 2.7(g).
Revised Table of Contents.
Revised para. 3.1.
Revised Table of Contents.
Revised para. 4.1 and para. 4.3.
Revised para. 4.5 (Normal Procedures Checklist).
Revised para. 4.7 and para. 4.9.
Revised para. 4.11.
Revised para. 4.17 and para. 4.19.
Revised para. 4.21.
Revised para. 4.39.
Revised para. 5.1 and para. 5.3.
Revised para. 5.5 (Flight
Planning Example).
Revised para. 6.1.
Revised para. 6.3.
Revised para. 6.5.
Revised Fig. 6-5.
Revised Weight and Balance Record;
added Title and Fig. no.
Revised Fig. 6-9.
Revised Fig. 6-11.
Revised para. 6.9.
Revised para. 7.15 (added Warning).
Revised para. 7.31.
Revised para. 8.1. '
Revised para. 8.3.
Revised para. 8.5.
Revised para. 8.2 l(b).
Revised para. 8.2 l(d).
Revised section 3, para. (a).
Revised Table of Contents.
Revised Title; revised para. 10.1 and para. 10.3.
Revised Title.
FAA Approval
Signature and
Date
UoaJL Gj-ti/rv*^
Ward Evans
Feb. 16, 1979
(\ i A /
D.H. Trompler
Jan. 13, 1989
Date
REPORT: VB-780
iv-a

V
TABLE OF CONTENTS
SECTION 1
GENERAL
Paragraph page
No. No-
Ll Introduction I'l
1.3 Engines I"3
1.5 Propellers 1-3
1.7 Fuel I-3
1.9 Oil I"3
1.11 ** Maximum Weights I"4
1.13 Standard Airplane Weights I"4
1.15 Baggage Space " I"4
1.17 " Specific Loadings I"4
1.19 Symbols, Abbreviations and Terminology 1-5
1.21 Conversion Factors 1-11
REPORT: VB-780

PIPER AIRCRAFT CORPORATION SECTION 1
PA-28-151, CHEROKEE WARRIOR GENERAL
SECTION 1
GENERAL
1.1 INTRODUCTION
This Pilot's Operating Handbook is designed for maximum utilization as an operating guide for the
pilot. It includes the material required to be furnished to the pilot by C.A.R. 3 and FAR Part 21, Subpart J.
It also contains supplemental data supplied by the airplane manufacturer.
This handbook is not designed as a substitute for adequate and competent flight instruction,
.knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars. It is
not intended to be a guide for basic flight instruction or a training manual and should not be used for
operational purposes unless kept in a current status.
Assurance that the airplane is in an airworthy condition is the responsibility of the owner. The pilot in
command is responsible for determining that the airplane is safe for flight. The pilot is also responsible for
remaining within the operating limitations as outlined by instrument markings, placards, and this
handbook.
Although the arrangement of this handbook is intended to increase its in-flight capabilities, it should
not be used solely as an occasional operating reference. The pilot should study the entire handbook to
familiarize himself with the limitations, performance, procedures and operational handling characteristics of
the airplane before flight.
The handbook has been divided into numbered (arabic) sections, each provided with a "finger-tip" tab
divider for quick reference. The limitations and emergency procedures have been placed ahead of the
normal procedures, performance and other sections to provide easier access to information that may be
required in flight. The "Emergency Procedures" Section has been furnished with a red tab divider to
present an instant reference to the section. Provisions for expansion of the handbook have been made by
the deliberate omission of certain paragraph numbers, figure numbers, item numbers and pages noted as
being left blank intentionally.
ISSUED: JUNE 17, 1976 REPORT: VB-780
1-1

SECTION 1
GENERAL
PIPER AIRCRAFT CORPORATION
PA-28-151, CHEROKEE WARRIOR
12' 11.75*
7 6"
Wing Area (sq. ft.)
Min. Turning Radius (ft.)
(from pivot point to wingtip)
170.0
30.0
STMIC 6R0UMO UHl-
r 3.6"
_J
THREE VIEW
Figure 1-1
REPORT: VB-780
1-2
ISSUED: JUNE 17, 1976

PIPER AIRCRAFT CORPORATION
PA-28-151, CHEROKEE WARRIOR '
SECTION 1
GENERAL
1.3 ENGINES
(a) Number of Engines
(b) Engine Manufacturer
(c) Engine Model Number
(d) Rated Horsepower
(e) Rated Speed (rpm)
(0 Bore (inches)
(g) Stroke (inches)
(h) Displacement (cubic inches)
(i) Compression Ratio
(j) Engine Type
I
Lycoming
O-320-E3D
150
2700
5.125
3.875
319.8
7:1
Four Cylinder. Direct Drive,
Horizontally Opposed, Air Cooled
1.5 PROPELLERS
(a) Number of Propellers
(b) Propeller Manufacturer
(c) Model
(d) Number of Blades
(e) Propeller Diameter (inches)
(1) Maximum
(2) Minimum
(f) Propeller Type
McCauley
1C160/EGM7653
2
76
74.5
Fixed Pitch
Sensenich
74DM6-0-58
2
74
72
Fixed Pitch
1.7 FUEL
AVGAS ONLY
(a) Fuel Capacity (U.S. gal) (total)
(b) Usable Fuel (U.S. gal) (total)
(c) Fuel Grade, Aviation
(1) Minimum Octane
(2) Specified Octane
(3) Alternate Fuel
50
48
80/87 Red
80/87 Red
Refer to Fuel Requirements,
Section 8 - Handling, Servicing and
Maintenance - paragraph 8.21, item (b).
1.9 OIL
(a)
(b)
(c)
Oil Capacity (U.S. quarts)
Oil Specification
Oil Viscosity per Average Ambient Temp, for Starting
SINGLE
(1) Above 60° F S.A.E. 50
(2) 30°Fto90°F S.A.E. 40
8
Refer to latest issue of
Lycoming Service Instruction 1014.
(3)
(4)
0°Fto 70° F
Below 10°F
S.A.E. 30
S.A.E. 20
MULTI
S.A.E. 40 or 50
S.A.E. 40
S.A.E. 40 or 20W-30
S.A.E. 20W-30
ISSUED: JUNE 17, 1976
REVISED: AUGUST 17, 1988
REPORT: VB-780
1-3

SECTION 1
GENERAL
PIPER AIRCRAFT CORPORATION
PA-28-151, CHEROKEE WARRIOR
1.11 MAXIMUM WEIGHTS
(a) Maximum Takeoff Weight (lbs)
(b) Maximum Landing Weight (lbs)
(c) Maximum Weights in Baggage Compartment
NORMAL
2325
2325
200
UTILITY
1950
1950
0
1.13 STANDARD AIRPLANE WEIGHTS*
(a) Standard Empty Weight (lbs): Weight of a
standard airplane including unusable fuel,
full operating fluids and full oil.
(b) Maximum Useful Load (lbs); The difference
between the Maximum Takeoff Weight and
the Standard Empty Weight.
1336
989
1.15 BAGGAGE SPACE
(a) Compartment Volume (cubic feet)
(b) Entry Width (inches)
(c) Entry Height (inches)
1.17 SPECIFIC LOADINGS
(a) Wing Loading (lbs per sq ft)
(b) Power Loading (lbs per hp)
24
22
20
\
13.7
15.5
•These values are approximate and vary from one aircraft to another. Refer to Figure 6-5 for the Standard
Empty Weight value and the Useful Load value to be used for C.G. calculations for the aircraft specified.
REPORT: VB-780
1-4
ISSUED: JUNE 17,1976
REVISED: FEBRUARY 16, 1979

PIPER AIRCRAFT CORPORATION
PA-28-151, CHEROKEE WARRIOR
SECTION 1
GENERAL
J^
1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
The following definitions are of symbols, abbreviations and terminology used throughout the
handbook and those which may be of added operational significance to the pilot.
(a) General Airspeed Terminology and Symbols
CAS Calibrated Airspeed means the indicated speed of an aircraft,
corrected for position and instrument error. Calibrated airspeed is
equal to true airspeed in standard atmosphere at sea level.
KCAS
GS
IAS
KIAS
M
TAS
VFE
vne/mne
VNO
VS
vS0
Calibrated Airspeed expressed in "Knots."
Ground Speed is the speed of an airplane relative to the ground.
Indicated Airspeed is the speed of an aircraft as shown on the
airspeed indicator when corrected for instrument error. IAS values
published in this handbook assume zero instrument error.
Indicated Airspeed expressed in "Knots."
Mach Number is the ratio of true airspeed to the speed of sound.
True Airspeed is the airspeed of an airplane relative to undisturbed
air which is the CAS corrected for altitude, temperature and
compressability.
Maneuvering Speed is the maximum speed at which application of
full available aerodynamic control will not overstress the airplane.
Maximum Flap Extended Speed is the highest speed permissible
with wing flaps in a prescribed extended position.
Never Exceed Speed or Mach Number is the speed limit that may
not be exceeded at any time.
Maximum Structural Cruising Speed is the speed that should not
be exceeded except in smooth air and then only with caution.
Stalling Speed or the minimum steady flight speed at which the
airplane is controllable.
Stalling Speed or the minimum steady flight speed at which the
airplane is controllable in the landing configuration.
Best Angle-of-Climb Speed is the airspeed which delivers the
greatest gain of altitude in the shortest possible horizontal
distance.
Best Rate-of-Climb Speed is the airspeed which delivers the
greatest gain in altitude in the shortest possible time.
ISSUED: JUNE 17,1976
REPORT: VB-780
1-5

SECTION 1
GENERAL
PIPER AIRCRAFT CORPORATION
PA-28-151, CHEROKEE WARRIOR
(b) Meteorological Terminology
ISA
OAT
Indicated Pressure
Altitude
Pressure Altitude
Station Pressure
Wind
International Standard Atmosphere in which:
The air is a dry perfect gas;
The temperature at sea level is 15° Celcius (59° Fahrenheit);
The pressure at sea level is 29.92 inches Hg. (1013.2 mb);
The temperature gradient from sea level to the altitude at which
the temperature is -56.5°C (-69.7°F) is -0.00198°C
(-0.003564° F) per foot and zero above that altitude.
Outside Air Temperature is the free air static temperature,
obtained either from inflight temperature indications or ground
meteorological sources, adjusted for instrument error and
compressibility effects.
The number actually read from an altimeter when the barometric
subscale has been set to 29.92 inches of mercury (1013.2 millibars).
Altitude measured from standard sea-level pressure (29.92 in. Hg)
by a pressure or barometric altimeter. It is the indicated pressure
altitude corrected for position and instrument error. In this
handbook, altimeter instrument errors are assumed to be zero.
Actual atmospheric pressure at field elevation.
The wind velocities recorded as variables on the charts of this
handbook are to be understood as the headwind or tailwind com
ponents of the reported winds.
.-"°'!^!*v
REPORT: VB-780
1-6
ISSUED: JUNE 17, 1976
REVISED: AUGUST 17, 1988

PIPER AIRCRAFT CORPORATION
PA-28-151, CHEROKEE WARRIOR
SECTION 1
GENERAL
(c) Power Terminology
Takeoff Power
Maximum Continuous
Power
Maximum Climb Power
Maximum Cruise Power
Maximum power permissible for takeoff.
Maximum power permissible continuously during flight.
Maximum power permissible during climb.
Maximum power permissible during cruise.
(d) Engine Instruments
EGT Gauge
Exhaust Gas Temperature Gauge
(e) Airplane Performance and Flight Planning Terminology
#
Climb Gradient
Demonstrated Crosswind
Velocity
Accelerate-Stop Distance
Route Segment
The demonstrated ratio of the change in height during a portion of
a climb, to the horizontal distance traversed in the same time
interval.
The demonstrated crosswind velocity is the velocity of the
crosswind component for which adequate control of the airplane
during takeoff and landing was actually demonstrated during
certification tests.
The distance required to accelerate an airplane to a specified speed
and, assuming failure of an engine at the instant that speed is
attained, to bring the airplane to a stop.
A part of a route. Each end of that part is identified by: (1) a
geographical location; or (2) a point at which a definite radio fix
can be established.
ISSUED: JUNE 17, 1976
REVISED: AUGUST 17, 1988
REPORT: VB-780
1-7

SECTION 1
GENERAL
PIPER AIRCRAFT CORPORATION
PA-28-151, CHEROKEE WARRIOR
(f) Weight and Balance Terminology
Reference Datum
Station
Arm
Moment
Center of Gravity
(C.G.)
C.G. Arm
C.G. Limits
Usable Fuel
Unusable Fuel
Standard Empty Weight
Basic Empty Weight
Payload
Useful Load
Maximum Ramp Weight
Maximum Takeoff
Weight
Maximum Landing
Weight
Maximum Zero Fuel
Weight
An imaginary vertical plane from which all horizontal distances are
measured for balance purposes.
A location along the airplane fuselage usually given in terms of
distance from the reference datum.
The horizontal distance from the reference datum to the center of
gravity (C.G.) of an item.
The product of the weight of an item multiplied by its arm.
(Moment divided by a constant is used to simplify balance
calculations by reducing the number of digits.)
The point at which an airplane would balance if suspended. Its
distance from the reference datum is found by dividing the total
moment by the total weight of the airplane.
The arm obtained by adding the airplane's individual moments and
dividing the sum by the total weight.
The extreme center of gravity locations within which the airplane
must be operated at a given weight.
Fuel available for flight planning.
Fuel remaining after a runout test has been completed in
accordance with governmental regulations.
Weight of a standard airplane including unusable fuel, full
operating fluids and full oil.
Standard empty weight plus optional equipment.
Weight of occupants, cargo and baggage.
Difference between takeoff weight, or ramp weight if applicable,
and basic empty weight.
Maximum weight approved for ground maneuver. (It includes
weight of start, taxi and run up fuel.)
Maximum weight approved for the start of the takeoff run.
Maximum weight approved for the landing touchdown.
Maximum weight exclusive of usable fuel.
,«»<?^v
REPORT: VB-780
1-8
ISSUED: JUNE 17,1976

PIPER AIRCRAFT CORPORATION SECTION 1
PA-28-151, CHEROKEE WARRIOR GENERAL
THIS PAGE INTENTIONALLY LEFT BLANK
ISSUED: JUNE 17, 1976 REPORT: VB-780

SECTION 1 pIpER AIRCRAFT CORPORATION
GENERAL PA-28-1S1, CHEROKEE WARRIOR
THIS PAGE INTENTIONALLY LEFT BLANK
;
REPORT: VB-780 ISSUED: JUNE 17, 1976
MO

PIPER AIRCRAFT CORPORATION
PA-28-151, CHEROKEE WARRIOR
SECTION 1
GENERAL
jg
1.21 CONVERSION FACTORS
MULTIPLY
atmospheres
centimeters
cm Hg
cm/second
cu centimeters
cuft
cu ft/min
cu in.
cu meters
cu yards
deg (arc)
BY
76.00
29.92
14.696
21,116
1.033
0.3937
3.281 x 10
1.934 x 10"
27.85
135.95
•2
3.281 x 10'
2.237 x 10
io"3
6.102 x 10
2.642 x 10'4
•2
-2
-2
2.832 x 10
1,728
3.704 x 10
7.481
28.32
4.719 x 101
2.832 xlO"2
16.39
1.639 x 10"
4.329 x 10
1.732 x 10"
-3
61,023
1.308
35.31
264.2
27.0
7.646 x 10*
2.022 x 10'
1.745 x 10
-2
TO OBTAIN
cm Hg at 0°C
in. HgatO°C
Ib/sq in.
lb/sq ft
kg/sq cm
in.
ft
lb/sq in.
lb/sq ft
kg/sq m
ft/sec
mph
liters
cu in.
U.S. gal
cu cm
cu in.
cu yards
U.S. gal
liters
liters/sec
cu m/min
cu cm
liters
U.S.gal
quarts
cu in.
cu yards
cuft
U.S. gal
cuft
cu meters
U.S. gal
radians
MULTIPLY
feet
ft/min
ft/sec
ft/lb
ft-lb/min
ft-lb/sec
fluid oz
gal, Imperial
gal, U.S. dry
gal, U.S. liquid
grams/cm
grams/cu cm
BY
3.048 x
3.333 x
1.894 x
1.646 x
1.136x
1.829 x
5.080 x
.6818
1.097
30.48
.5925
1.383 x
3.030 x
1.818x
8
29.6
277.4
1.201
4.546
268.8
1.556 x
1.164
4.405
231.0
1.337 x
3.785
8.327 x
1.280 x
0.1
6.721 x
5.601 x
1,000
62.43
10"1
10"1
10"4
10"4
IO2
io-2
IO1
10'1
10s
io"3
io1
io1
io-;
io2
io-2
io3
TO OBTAIN
meters
yards
miles
nautical miles
mph
km/hr
cm/sec
mph
km/hr
cm/sec
knots
m-kg
hp
hp
dram
cu cm
cu in.
U.S. gal
liters
cu in.
cuft
U.S. gal liquid
liters
cu in.
cuft
liters
Imperial gal
fluid oz
kg/m
lb/ft
lb/in.
kg/cu m
lb/cu ft
ISSUED: JUNE 17, 1976
REPORT: VB-780
1-11

SECTION 1
GENERAL
MULTIPLY
horsepower
horsepower, metric
inches
in. Hg at 0°C
kilograms
kg-calories
kg/cu m
kg/sq cm
kilometers
km/hr
knots
BY
33,000
550
76.04
1.014
75.0
9.863 x
2.540
83.33 x
3.342 x
4.912 x
70.73
3.453 x
2.205
35.27
103
3087
4.269 x
62.43 x
lO"3
14.22
2.048 x
28.96
3.281 x
6.214 x
5.400 x
105
9.113x
5.396 x
6.214 x
2.778 x
1.0
1.688
1.151
1.853
5.148 x
lC-3
io-;
10"'
io2
10
io"3
io3
10,
io1
io-
lO"1
10'
io-
io-
io-
•
TO OBTAIN
ft-lb/min
ft-lb/sec
m-kg/sec
metric hp
m-kg/sec
hp
cm
ft
atmospheres
lb/sq in.
lb/sq ft
kg/sq m
lb
oz
grams
ft-lb
m-kg
lb/cu ft
grams/cu m
lb/cu ft
lb/sq ft
in. Hg at 0°C
ft
miles
nautical miles
centimeters
ft/sec
knots
mph
m/sec
nautical mph
ft/sec
mph
km/hr
m/sec
PIPER AIRCRAFT CORPORATION
PA-28-151, CHEROKEE WARRIOR
MULTIPLY
liters
meters
meter-kilogram
meter/sec
microns
miles
mph
miles/hr sq
milibars
nautical miles
ounces, fluid
lb/cu ft
lb/cu in.
BY
IO3
61.03
3.532 x 10
2.642 x IO"1
2.200 x IO"1
1.057
39.37
3.281
1.094
6.214x 10
7.233
3.281
2.237
3.600
3.937 x 10
5280
1.609
8.690x10
1.467
4.470 x 10'1
1.609
8.690 xlO1
2.151
2.953 x IO'2
6076.1
1.151
1852
29.57
1.805
16.02
1728
27.68
TO OBTAIN
cu cm
cu in.
cuft
U.S. gal
Imperial gal
quarts
in.
ft
yards
miles
ft-lb
ft/sec
miles/hr
km/hr
in.
ft
km
nautical miles
ft/sec
m/sec
km/hr
knots
ft/sec sq
in. HgatO°C
ft
miles
m
cu cm
cuin.
kg/cu m
lb/cu ft
grams/cu cm
1
^
REPORT: VB-780
1-12
ISSUED: JUNE 17, 1976