Cessna 172 P Technical specifications

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1981 MODEL 172P
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30 May 1980

THIS MANUALWAS PROVIDED FOR THE A¡RPLANE
IDENT¡FIED ON THE TITTE PAGE ON
SUBSEOUENT REVISIONS SUPPLIED BY CESSNA
AIRCRAFT COMPANY MUST BE PROPERLY IN.
SERTED.
CESSNA AIRCRAFT COMPANY, PAWNEE DIVISION
\/

.f
CESSNA
MODEL 172P CONGN,ATI'LATIONS
aaaa
CONCRATULATIONS
Welcome to the ranks of Cessna ownersl Your Cessna has been designed and
constructed to give you the most ¡n performance, economy, and comforl. lt is our desire that
you will find fly'ing ít, either for buiiness or pleasure, a pleasant and profitable experience.
This a guide to helP You get the most
pleasure ormation about your Cessna's
äquipme suggestions for its servicing and
caie. We refer to it frequentlY.
Our ¡nterest in your flying pleasure has not ceased with your purchase of a Cessna.
World-wide, the Ceisna Dealer Organization backed by the Cessna Customer Services
Department stands ready to serve you. The following services are offe¡ed by most Cessna
Dealers:
a FACTORY TRAINED PERSONNEL to provide you with courteous expert service.
. TACTORY APPROVED SERVICE ËQUIPMENT to provide you efficient and accurate
workmanship.
a A STOCK Ot CENUINE CESSNA SERVICE PARTS on hand when you need them.
. THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING CESSNA AIR-
PLANES, since Cessna Dealers have all of the Service Manuals and Parts Catalogs, kept
current by Service Letters and Service News Letters, published by Cessna Aircraft
Company.
We urge all Cessna owners to use the Cessna Dealer Organization to the fullest.
A current Cessna Dealer Directory accompanies your new airplane. The Directory is
revised f requently, and a current copy can be obtained from your Cessna Dealer. Make your
D¡rectory one of your cross-country flight planning aids; a warm welcome awaits you at
every Cessna Dealer.
)
80 May 1980

PERFORMANCE-
SPECIFICATIONS
7õ7o Powet at 8000 Ft
50 ea,llons Usable Fuål
761o Powet at 8000 Ft
62 Glallons Usoblo Fuel
Maximum Range at 10,000 Ft
40 Gallous Ueable FueI
Maximum Range at 10,000 Ft
50 Gallons Usable Fuel
Maximum Ilange at 10,000 Ft
62 Clellons Usable FueI
N,ATE OF CLIMB AT SEA LEVEL
SERVICE CEILING
TAKEOFF PER,FOH,MANCE:
Ground Roll
Total Distance Over 50-F t Obstacle
I,ANDING PER,FOR,MANCE ¡
Ground Roll
Total Distanco Over õ0-Ft Obst¿cle
STALL SPEED (KCAS):
Flaps Up, Power Off
Flaps Down, Power Pff
MAXIMUM WEIGHT:
Remp
raÈeãttorLandinj::::
STANDARD EMPTY WEIGHT:
Skyhawk
Skyhawk II
MAXIMUM USEFUL I,OAD:
Skyhowk
Range 58ó NM
Timo õ.0 HRS
Range
Time
Rango
Tlmo
Range
Time
F,ange
.tï. .
::::
CESSNA
MODEL 172P
PERFORMANCE - SPECIFICATIONS
SPEED:
Maximum at Soa Level .1Zg KNOTS
Cruis 0 Ft .120 KNOTS
CRUISE: mixture with fuel allowancefor engine
cllmb and 45 minutes reserve.
767o Power at 8000 Ft Range 440 NM
40 Clallons Usable Fuel Timõ g.B HRg
75õ NM
6.4 HRS
õSO NM
õ.8 HRÉI
680 NM
7.4 HRS
875 NM
9.4 HRS
.7OO FPM
.13,000 FT
.890 FT
.1825 FT
.540 FT
.1280 FT
.51 KNOTS
.46 KNOTS
Skyhawk II
BAGGAGEALLOWAÑCb' : :
WÍNG LOADING: Pounds/Sq Ft
PO1üER LOADIÑG: Pounds/HP
FUEL CAPACITY: Total
Standard Tanks
Long Range Tanks
Integral Tanks
OTL CAPACITY
ENGINE: Avco Lycoming
160 BHP ôt 2700 RPM
PROPELLER: Fixed Pitch, Diameter
. .2407 LBS
. .2400 LBS
1414 LBS
1440 LBS
.993 LBS
.967 LBS
.120 LBS
.13.8
.15.0
.43 GAL.
.õ4 GAL.
.88 GAL.
.8 QTS
.o-320-DAJ
. .75IN.
Tho ebovo porlor:mrnoe llgureg Brs brsed on the lndlcet¿d welghte, stenda.rd oboepherlo
oondltloae, level hs¡d-surlsoo dql¡ rutrw&ya, o¡rd no wlnd. They s¡e o¡lcul¿ted v¡lue¡
derlved tron flþht teets oonductod by the Cee¡¡¿ Airorelt Company under ca,refully
doorño[3ed oondltlone ¡,nd will vor¡l wlth l¡dlvldu¡l alrplanee ¡nd numerous l¡¡to¡¡
afleotlng lllght pedoturnoe,
lt 30 May 1980

CESSNA COVERAGEIBEVISIONS/
MODEL1?2P LOGOFEFFFECTIVEPAGES
COVERAGE
The Pilot'g Operating Handbook iu the airplane ¿t the time of delivery from Ceesna Ai¡craft
Company contains information applicable to the 1981 Model 1?2P airplaue deeignated by the serial
number aud regietration numbe¡ shown on the Title Page of this handbook. This information is based
o¡ data available at the time ofpublication.
REVISIONS
Chauges and/or additiong to thia handbooL will be covered by revisione published by Cesena
Aircraft Company. These ¡evisiona are diet¡ibuted to ow¡ers ofU.S. Regietered ai¡c¡aft accordiag to
FAA recorils aü the time of revision iseuauce, and to Iut¿rnationally Registered aircraft according to
Ce¡sna Owne¡ Advisory recorde aü the time ofissuance,
Revisions ¡hould be examined immediately upon receipt aud incorporated in thíe handbook.
NOTE
It le tho responsiblllty of the owner to maintain thle handbook ln a
curlent statu€ when it ie being ueed for operatlonal purposos.
Owners shoulil contact thei¡ Ceasna Service Station whenever the revisioË statue of theirl
handbook is in question.
A revision bar will extend the full length ofnew or revised text and/or illwtratione added on new
or presently exiating pages. This bar will be located a{iacent to the applicable revised area on the outer
margin ofthe page,
All revised pages will carry the revieion number and date ou the applicable page.
The following Log ofEffective Pagea provides the dates ofissue for original and revised pages, and
a listing of all pages in the handbook. Pages affected by the current revision are indicatcd by an
asterisk (*) preceding the pagee liated.
LOG OF EFFECTIVE PAGES
Dates ofissue for original and revised pages:
Original
Revision I. 30 May 1980
I December 1983
Date
. 30 May 1980
. 30 May 1980
. 30 May 1980
I October 1994
. 30 May 1980
. 90 May 1980
. 30 May 1980
. 00 May 1980
. 30 May 1980
. 30 May 1980
I October 1994
. 30 May 1980
. flO May 1980
Revision 2
Page ....
1 October 1994
Pâge ...
fitle ...
Assignment Rncord
ith¡uü.
* iii ...
iv .....
l-1 th¡u l-9 . ......
1-10 Blank
2-I ....
2-2 Blank
2-3 th¡u 2-4 .. .,.. .
+ 2-6thru2-6 ....,..
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Datè
80 May 1980
30 May 1980
30 May 1980
I Octobe¡ 1994
80 May 1980
.30 May 1980
30 May 1980
I Octobe¡ 1994
30 May 1980
30 May 1980
30 May 1980
80 May 1980
30 May 1980
30 May 1980
30 May 1980
30 May 1980
30
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30
s0
30
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30
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May 1980
May 1980
May 1980
May 1980
May 1980
May 1980
May 1980
May 1980
NOTD
Refer to Section 9 Table of0ontents for
supplementa applcable to optional systems.
30 May 1980
Revieion2 -1October1994 (Rcl-25-04/03) lll

TABLE OFCONTENTS CESSNA
MODEL 172P
7
I
TABLE OF CONTENTS
SECTION
GENERAL 1
LIMITATIONS 2
EMERGENCY PROCEDURES 3
NORMAL PROCEDURES 4
PERFORMANCE 5
WEIGHT & BALANCE /
EOUIPMENT LIST 6
AIRPLANE & SYSTEMS
DESCRIPTIONS
AIRPLANE HANDLING,
SERVICE & MAINTENANCE
SUPPLEMENTS
(Optional Systems Description
& Operating Procedures) ¡ ¡ . I
lv 30 May 1980

CESSNA
MODEL 17UP SECTION 1
GENERAL
Page
t-2
1-3
1-8
1-3
1-3
1-S
l-4
1-5
1-5
1-5
1-5
1-5
1-6
1-6
1-6
r-7
t-7
1-8
SECTION 1
CENERAL
)
TABLE OF CONTENTS
Three View
Introduction . .
Doscriptive Data
Engine
Propeller
Fuel
oil
Maximum Certifioated Iüeights
Standard Airplane \lleigbts
Cabin And Entry Dimensions
Baggage Space And Entry Dimensions
Specific Loadings
Symbols, Abbreviations And Terminology
General Airspeed Terminology And Symbols
Meteorolo gical Terminolo glr
Engine Power Terminology
Airplane Performance A'nd Flight Planning Terminology
lÃleight And Balance Terminology
30 May 1980 1-1

SECTION 1
GENER,AIJ
NOTES:
2. M¡x¡mum hs¡0ht ¡hom wlth næ
gcr depË*d, all tlræ ônd nor
nrut proporly lnllEtôd, ond flðhlng
òB@n in¡t¡lhd.
3. '!!hæl bæ lsngth l¡ 6õ".
4. Prop€llor ground clsEnæ lt 111".
5, Wng rro ls 174 qu¡ro læt.
6, Mlnlmum tunlng rldlur | * plvot
polnt to outbmrd wlng tlpl 13
27',-5ß".
'-1 1
14
76"
1/2"
CESSNA
MODEL 172P
1/2"
1
PIVOT POINT
*PIVOT POINI *
o
o
t-2
Figure 1-1. Three View
80 May 1980

CESSNA
MODEL 172P E¡ECTION 1
GENER,AL
INTRODUCTION
This handbook contains g sections, and inoludes the material required
to be furnished to the pilot by CAR Part 3. It also contains supplemental
data supplied by Cessna Aircraft Company.
Section 1 provides basic data and information of general interest. It
also contains definitions or explanations of symbols, abbreviations, and
terminology commonly used.
DESCRIPTIVE DATA
ENGINE
Number of Engines: 1.
Engine Manufacturer: Avco Lycoming.
Engine Model Number: O-840-D2J.
Elngine Type: Normally-aspirated, diqect-drive, air-cooled, horizontally-
opposed, oarburetor equipped, four-cylinder engine with 819.8 cu. in.
displacement.
Horsepower Rating and Engine Speedl 160 rated BHP at 2700 RPM.
PROPELLER
Propeller Manufacturer: McOauley Aocessory Division.
Propeller Model Number: 1C160/DTM7557.
Number of Blade* 2.
Propeller Diametor, Maximum; ?B inches.
Minimumi 74 inches.
Propeller Type: Fixed pitch.
FUEL
Approved Fugl Grades (and Colors):
100LL Grade Aviation Fuel (Blue).
100 (Formerly 100/ 130) Grade Aviation Fuel (Greon).
NOTE
Isopropyl alcohol or ethylene glycol monomethyl ether
may be added to the fuel supply. Additive concentrations
shall not exceed LVo for isopropyl alcohol or .I6Vo f.or
ethylene glycol monomethyl ether. Refer to Section g for
additional information.
30 May 1980 1-3

SECTION 1
GENEN,AL
Sump
Total: 7 Quarts
I Quarts.
Fuel Capaoit¡r:
Standard Tanks:
Total Capacity: 43 gallons.
Total Capacity Each Tank 21.5 gallons.
Total Usable: 40 gallons.
Long Range Tanks:
Total CapacÍty: õ4 gallons.
Total Capacity Each Ta,nk 27 gallons.
Total Usable: õ0 gallons.
Integral Tanksl
Total Capacity: 68 gallons.
Total Capaoity Each Tank: 34 gallons.
Total Usable: 62 gallons. NOTE
To ensure maximum fuel capacity when refueling and
minimize cross-feeding when parked on a sloping surface,
place the fuel selector valve in either LEFT or RIGHT
position.
otL
Oil Grade (Specification):
MIL-L-6082 Aviation Grade Straight Minoral OiL Use to replenish
supply duríng first 25 hours and at the first 2õ-hour oil change.
Continue to uso until a total of õ0 hou¡s has aooumulated or oiÌ
consumption has stabilized.
MIL-L-22851 Ashless DÍsporsant Oil: This oil muat be used after first õO
hours or oil consumption has stabilized,
Recommendod Viscosity for Temperature Range:
MIL-L-6082 Aviation Grade Straight Mineral Oil:
AII temporatures, use SAE 20W-õO or
Above 16oC (60oF), use SAE 50
-lo0 (30"F) to 32oC (90'F), use SAE 40
-18"C (0'F) to 21oC (70'F), use SAE 30
Below -12'C (10"F), use SAE 20
MIL-L-228õ1 Ashless Dispersant Oil:
AII temperatures, use SAE 20ïV-50 or
Above 16oC (60oF), use SAE 40 or SAE õ0
-1"C (30'F) to 32oC (90'F), use SAE 40
-18oC (OoF) to 21oC (70'F), use SAE 40 or SAE 30
Below -12oC (10oF), use SAE 30
OiI Capacity:
CESSNA
MODEL 172P
t-4 30 May 1980

CESSNA
MODEIJ 1?2P
Standard Empty Weight, Skyhawk: 1414Ibs.
Skyhawk II: 1440lbs.
Maximum Useful Load: Normal Category
Skyhawk: 993lbs.
Skyhawk II: 967lbe.
SECTION 1
GENERAL
MAXIMUM CERTIFICATED WEIGHTS
Ramp, Normal Category: 2407 lbs.
Utitity Category: 2107 lbs.
Takeoff, Normal Category:2400 lbs.
Utility Category: 2100 tbs.
Landing, Normal Categoryr 2400 lbs.
Utility Category: 2100 lbe.
Weight in Baggage Compartment, Normal Category:
Baggage Area 1 (or passenger on chÍld's seat) - Station 82 to 108; 120
lbs. See note below.
Baggage Area 2 - Station 108 to L42: õO lbs. See note below,
NOTE
The maximum combined weight capacity for baggage
areas 1 and 2 is 120 lbs.
Weight in Baggage Compartment, Utility Category: In this category, the
baggage compartment and rea,r seat must not be occupied.
STANDARD AIRPLANE WE¡GHTS
Utifi$ Category
693 lbs.
667 lbs.
CABIN AND ENTRY DIMENSIONS
Detailed dimensions of the cabin interior and ontry door openings are
illustrated in Section 6.
BAGGAGE SPACE AND ENTRY DIMENSIONS
Dimensions of the baggage
illustrated in detail in Section 6. area and baggage door opening are
SPECIFIC LOADINGS
Wing Loading: 13.8 lbs,/sq. ft.
Power Loading: 15.0 lbs./hp.
30 May 1980 1-5

SECTION 1
GENERAL CEggNA
MODEIJ 172P
SYMBOLS, ABBREVIATIONS AND
TERMINOLOGY
GENERAL A¡RSPEED TERM¡NOLOGY AND SYMBOLS
KcAs Knots collbrated Alrspeed is indicated airspeed oorrected
for position and instrument error a,nd expreesed in knots.
Knots oalibrated airspeed is equal to KTAS in standard
atmosphere at sea lovel.
KIAS Knots Indicated Airspeed is the speed shown on the
airspeed indicator and expreesed in knots.
KTAS Knote Tme Airspeed is the airspeed expressed in knots
relative to undisturbed air whioh is KCAS corrected for
altitude and temperature.
VA Manuevering Speed is the maximum speod at which you
ma,y use abrupt oontrol travel.
Vf,g Maximum Flep Extended Speed is the !Íghest speed
permissiblo with wing flaps in a prescribed extended
position.
V*o Maximum Structural Gruising Speed is the speed that
shouldnot be oxceededexcept in smooth air, then onlywith
caution.
VNp Never-Exceed Speed is the speed limit that may not be
exceeded at any time.
VS Stalling Speed or trhe mi¡lmun steady f,ight speed at
which the airplane is controllable.
VS^ Stalltng Speed or the mlnimum eteady flight epeed at
' which the airplane is controllable in the landing configu-
ration at the most forward center of gravity.
V"' Best Angle-of-Climb Speed is the speed which results in
the greatest gain of altitude in a given horizontal dÍstance.
Vv Best Rate-of-Climb Speed is the speed which results in the
- Createst gain in altitude in a given time.
METEOROLOGICAL TER MINOLOGY
OAT Outside Air Tempereture is the free air static temperature.
1-6 30 May 1980

CEggNA
MODEL 172P
Standard
Tempera-
ture
Pressure
Altitude
BHP
R,PM
Static
RPM
Demon-
strated
Crosswind
Velocity
Usable FueI
Unusable
Fuel
GPH
NMPG
ú
Þ
It is expressed in either degrees Celsius or degrees Fah-
renheit.
Stand¡rd Temperature is 15oC a,t sea, level pressure alti-
tude and decreases by ZoC for each 1000 feet of altitude.
SECTION 1
GENERAL
Bral¡e lloreepower is the power developed by the engine,
Revolutlons Per Mlnute ís engine speed.
Static RPM is engine speed attained during a full-throttle
engine runup when the airplane is on the ground and
stationary.
Demonstrated Croesrrind Velocit¡r is the velocity of the
crosswind oomponent for which adequate control of the
airplane during takeoff and landing was actually demon-
strated during certification tests. The value shown is not
considered to be limiting.
Usable Fuel is the fuel available for flight planning.
Unusable Fuel is the quantifV of fuet that can not be safely
used in flight.
Gallone Per Hour is the amount of fuel (in gallons)
consumed per hour.
Nautical Miles Per Gallon is the distance (in nautical
miles) which can bo expected per gallon of fuet cousumed
at a specific engine power setting and/or flight configura-
tion.
P¡es¡u¡e Ntltude is the attitude read from an altimeter
when the altimeter's barometric scale has been set to 29.92
inches of mercury (1018 mb).
ENGINE POWER TERMINOLOGY
)AIRPLANE PERFORMANCE AND FLIGHT PI.ANNING
TERM¡NOLOGY
30 May 1980
g is acceleration due to gravity
1-7

WEIGHT AND BALANCE TERMINOLOGY
Reference Reference Datum ls an lmaglnary vertloal plane from
Datum which all horizontal distances are mea,sured for balance
purposes.
Station Station is a location along the airplane fuselage given in
terms of the distance from the retorenoe datum.
SECTION 1
GENERAL
Arm
Moment
Center of
Gravity
(c.G.)
c.G.
Arm
c.G.
Limits
Standard
Empty
Weight
Basic Empty
Weight
Useful
Load
Maximum
Ramp
Weight
Maximum
Takeoff
Weight
CESSNA
MODEL 1?2P
Arm is the horizontal distance from the reference datum to
the center of gravity (C.G.) of an ltem.
Moment is the product of the weight of an item multiplied
by its arm. (Moment divided by the sonstant 1000 is used i.n
this handbook to simplify balance calculations by reduc-
ing the number of digits.)
Center of Gravity is tho point at which an airplane, or
equipment, would balance if suspended. Its distance from
the refergnce datum is found by dividing the total moment
by the total weight of the airplane.
Center of Gravlty A¡rn is the arm obtained by adding the
airplane's individual moments and dividing the sum by
the total weight.
Center of Gravlty Limits are the extreme conter of gravity
losations within which the airplane must be operated at a
given weight.
Standa¡d Empty llleight is the weight of a stanclard air-
plane, including unusable fuel, full operating fluids and
full engine oil.
Basic Empty llfeight is the standard empty weight plus tlre
weight of optional equipment.
Useful Load is the difference between ra,mp weight and the
basic empty weight.
Maximum Romp Weight is the maximum weight approved
for ground maneuver. (It includes the weight of start, taxi,
and runup fuel.)
Maximum Tal¡eoff Weight is the maximum weight ap-
proved for the start of the takeoff run.
1-8 30 May 1980

CESSNA
MODEL 17¿P
Maximum
Landing
Weight
Tare
SEICTION 1
C}E!NER,AI.,
Maximum Landing trletght is the maximum weight ap-
proved for the landing touchdown.
Tare is the weight of chooks, blooks, stands, etc. usedwhen
weighing an airplane, and is included in the scale read-
ings. Tare is deducted from the sca,le reeding to obtain tho
actual (net) airplane weight.
30 May 1980 1-9l(1-10 blank)

CESSNA
MODEL 172P
TABLE OF CONTENTS
Introduction
Airspeedlimitations . . .
Airspeed Indicator Markings
Power Plant Limitations
Power Plant Instrument Markings
Weight Limits
Normal Category
Utility Category
Center Of Gravity Limits
Norrnal Ca,tegory
Utility Category
Maneuver Limits
Normal Category
UtÍlity Category
Flight Load Factor Limits
Norrnal Category
Utility Category
Kinds Of Operation Limits
FueI Limitations
Other Linitations :
Flap Limitations
Placards
SECTION 2
LIMITATIONS
SECTION 2
LIMITATIONS
Page
2-3
2-4
2-4
2-6
?.6
2-6
2-6
2-7
z-7
2-7
z-7
2-7
2-7
2-7
2-8
2-8
2-8
2-S
z-g
u-10
2-10
2-10
30 May 198O P.-11(2-2 blank)

CESSNA
MODEL 172P SECTION 2
LIMITATIONS
INTRODUCTION
Section 2 includes operating limitations, ihstrument markings, and
basic placards neoessary for the safe operation of the airplane, its engine,
standald systems and standard equipment. The limitations included in
this section and in Section g have been approved by the Federal Aviation
Administration. Obsenrance of these operating limitations is required by
Federal Aviation Regulations.
NOTE
F,efer to Section I of this Pilot's Operating Handbook for
amended operating limitations, operating procedures,
performance dqta and other necessary information for
airplanes equippod with specific options.
NOTE
The airspeeds listed in the Airspeed Limitations chart
(figure 2-1) and the Airspeed Indicator Markings chart
(figure 2-2) are basod on Airspeed Calibration data shown
in Section 5 with the normal static source. If the alternate
static source is being used, ample margins should be
observed to allow for the airspeed calibration variations
between the normal and alternate static sources as shown
in Section õ.
Your Cessna is certíficated under FAA Type Certificate No. 3412 as
Cessna Model No. 172P.
30 May 1980 ?'-3

SECTION 2
LIMITATIONS CESSNA
MODEL 172P
AIRSPEED LIMITATIONS
Airspeed li¡nitations and tl¡eir operatioual aignifioance are sbown in
figure 2-1. Maneuvering speeds shown apply to normal cetegory opeta,-
tions. The utility aa,togory m&neuvering speed is 102 KIAS at2lü)pounds.
Figure 2-1. Airspeed Limitations
AIhSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code significance are
shown in figure 2-2.
SPEED KCAS KtAS REMARKS
VNe Never Exceed Speed 152 158 Do not exceed this speed in
any operat¡on.
Vruo Maximum Structural
Cruising Speed 123 127 Do not exceed this speed
except in smooth air, and
then only with caution.
V¡ Maneuvering Speed:
2400 Pounds
20ü) Pounds
16ü) Pounds
97
91
81
99
92
82
Do not make full or abrupt
control movements above
this speed.
Vre Maximum Flap Extended
Speed:
loo Flaps
loo - 3oo Flaps 108
84 110
85 Do not exceed this speed
with flaps down.
Maximum Window Open
Speed 162 158 Do not exceed this speed with windows open.
2-4 30 May 1980