Cessna Skyhawk 172N 1980 Quick setup guide

INFORMATION
MANUAL
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MODEL
172N
SKYHAwK
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Lessna

NOTICE
AT THE TIME OF ISSUANCE, THIS INFOR-
MATION MANUAL WAS AN EXACT DUPLI-'
CATE OF THE OFFICIAL PILOT'S OPERAT-
ING HANDBOOK AND FAA APPROVED
AIRPLANE FI.IGHT MANUAL AND !S TO BE
USED FOR GENERAL PURPOSES ONLY.
IT WILL NOT BE KEPT iunRENT AND,
THEREFORE; CANNOT BE USED AS A
SUBSTITUTE FOR THE OFFICIAL PILOT'S
OPERATING HANDBOOK AND FAA
APPROVED AIRPLANE FLIGHT MANUAL
INTENDED FOR OPERATION OF THE AIR.
PLAN E.
CESSNA AIRCRAFT COMPANY
1 JULY 1979

PERFORMANCE.
SPECIFICATIONS CESSNA
MODEL 172N
PERFORMANCE . SPECI FICATIONS
SPEED:
Maximum at Sea Level 125 KNOTS
Cruise, 757o Power at 8000 Ft . 122 KNOTS
CRUISE: Recommended lean mixture with fuel allowance for engine
start, taxi, takeoff, climb and 45 minutes reserve.
75Vo Power at 8000 Ft . Range
40 Gallons Usable Fuel Time
75Vo Power at 8000 Ft . Range
SERVICE CEILING 14,200 FT
TAKEOFF PERFORMANCE:
Obstacle
Ground RoII ' 520 FT
50 Gallons Usable Fuel
Maximum Range at 10,000 Ft
40 Gallons Usable FueI
Maximum Range at 10,000 Ft
50 GaIIons Usable Fuel
RATE OF CLIMB AT SEA LEVEL
Time
Range
Time
Range
Time
455 NM
3.8 HRS
600NM
5.0 HRS
575 NM
6.1HRS
750 NM
7.9 HRS
770 FPM
775 FT
1390 FT
1250 FT
50 KNOTS
44 KNOTS
2307 LBS
23OO LBS
Ground RoII
Total Distance Over 50-Ft
LANDING PERFORMANCE:
Total Distance Over 50-Ft Obstacle
STALL SPEED (CAS):
Flaps Up, Power Off
Flaps Down, Power Off
MAXIMUM WEIGHT:
Ramp
Takeoff or Landing
STANDARD EMPTY WEIGHT:
Skyhawk
Skyhawk II
MAXIMUM USEFUL LOAD:
Skyhawk
Skyhawk II
BAGGAGE ALLOWAI\iCb
WING LOADING: Pounds/Sq Ft
POWER LOADING: Pounds/HP
FUEL CAPACITY: Total
Standard Tanks
Long Range Tanks
OIL CAPACITY
ENGINE: Avco Lycoming
160 BHP at 2700 RPM
1403
1430 LBS
LBS
904 LBS
877 LBS
120 LBS
13.2
t4.4
43 GAL.
54 GAL.
6 QTS
o-320-HzAD
PROPELLER: Fixed Pitch, Diameter 75 IN.
The above performance figures are based on the indicateq weig-hts, standa-rd atmospheric
conditions] level hard-suiface dry runways, and no wind. They are calcufated values
derived from flight tests conducded by the Cessna Aircraft Company under carefully
document€d conditions and will vary with individual airplanes and numerous factors
affecting flight performance.
t JuIy 1979

INFORMATION MANUAL
CESSNA AIRCRAFT COMPANY
19BO MODEL 172N
coPYRtcHT o 1979'
CESSNA AIRCRAFT COMPANY
W]CHITA, KANSAS, USA
THE REPRINTING OF THIS MANUAL INCORPO-
RATES INFORMATION ISSUED IN REVISION 1
DATED 15 NOVEMBER 1979 FROM THE PILOT'S
OPERATINC HANDBOOK AND FAA APPROVED
AIRPLANE FLICHT MANUAL.
llr
Q n.^t", ol GAMA
Dl 1 72- 13-RPC -2500-3 / 9 1
i-"

CESSNA
MODEL 172N
1 JuIy 1979
SECTION 1
GENERAL
SECTION 1
GENERAL
TABLE OF CONTENTS Page
Three View L-z
Introduction I-3
Descriptive Data 1-3
Engine 1-3
Propeller 1-3
Fuel 1-3
oil 1-4
Maximum Certificated Weights 1-5
Standard Airplane Weights 1-5
Cabin And Entry Dimensions 1-5
Baggage Space And Entry Dimensions 1-5
Specific Loadings 1-5
S5rmbols, Abbreviations And Terminology 1-6
General Airspeed Terminology And Symbols 1-6
Meteorological Terminology . 1-6
Engine Power Terminology l-7
Airplane Performance And Flight Planning Terrninology t-7
Weight And Balance Terminology 1-8
1-1
l-

SECTION 1
GENERAL
t-2
CESSNA
MODEL 172N
3.
4.
5.
6.
Figure 1-1. Three View
9 t/2" t AX
NOTES:
l. Wing span shown with slrobe lights
installed.
2. Maximum h€ighl shown wilh nose
gEar depre$ed, all tires and nose
srut properlv in{lated. and flashing
beacon rnstalled,
Whel ba* length as 65".
Prorller qround clearance is 1 1 3/4".
Wing area is 174 square fet.
Minimum turning radiua ( *pivot poinr
to outboard wing tip) is27'-5 112".
1 July 1979

CESSNA
MODEL 172N SECTION 1
GENERAL
INTRODUCTION
This handbook contains 9 sections, and includes 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 -.f
Number of Engines: 1. ,! '$ |
Engine Manufacturer: Avco Lycoming. ,
Engine Model Number: O-320-H2AD.
Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally-
opposed, carburetor eguipped, four-cylinder engine with 320 cu. in.
displacement.
Horsepower Rating and Engine Speed: 160 rated BHP at ZZ00 RpM.
PROPELLER
Propeller Manufacturer: McCauley Accessory Division.
Propeller Model Number: 1C160/DTM7557.
Number of Blades: 2.
Propeller Diameter, Maximum: 75 inches.
Minimum: 74 inches.
Propeller Type: Fixed pitch.
FUEL
Approved Fuel Grades (and Colors):
100LL Grade Aviation Fuel (Blue).
100 (Formerly 100/ 130) Grade Aviation Fuel (Green).
NOTE
Isopropyl alcohol or ethylene glycol monomethyl ether
rnay be added to the fuel supply. Additive concentrations
shall not exceed lo/o for isopropyl alcohol or .157r for
ethylene glycol monomethS,zl ether. Refer to Section 8 for
additional information.
1 JuIy 197s 1-3

SECTION 1
GENERAL
Fuel Capacity:
Standard Tanks:
Total Capacity: 43 gallons.
Total Capacity Each Tank 21.5 gallons.
Total Usable: 40 gallons.
Long Range Tanks:
Total Capacity: 54 gallons.
Total Capacity Each Tank:. 27 gallons.
Total Usable: 50 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-22851 Ashless Dispersant Oil: The airplane was delivered from
the factory with SAE 20W-50 ashless dispersant aircraft engine oil.
Ashless dispersant aircraft engine oil must be used for all operat-
ing conditions. NOTE
Use a minimtrr, of.75Vo power for cruise during the first 50
hours of operation or until oil consumption stabilizes'
Service the engine oil system with aviation ashless dis-
persant oil only.
Required Viscosity for Temperature Range:
MIL-L-22851 Ashless Dispersant OiI:
SAE 20W-50 or SAE 15W-50 for all temperatures.
NOTE
If multi-viscosity ashless dispersant aircraft engine oil is
not available, the following ashless dispersant aircraft
engine oil may be used.
SAE 50 above 60'F (16'C).
SAE 40 between 30"F (-1"C) and 90oF (32'C).
SAE 30 between OoF (-18'C) and 70oF (21'C).
SAE 20W-30 below 0"F (-18'C) to 70oF (21oC).
OiI Capacity:
Sump: 6 Quarts.
Total: 7 Quarts (if oil filter installed).
t-4
CESSNA
MODEL 172N
1 July 1979
Revision 1 - 15 November 1979

CESSNA
MODEL 172N SECTION 1
GENERAL
MAXIMUM CERTIFICATED WEIGHTS
Ramp, Normal Category: 2307 lbs.
Utility Category: 2007 lbs.
Takeoff, Normal Category: 2300 lbs.
Utility Category: 2000 lbs.
Landing, Normal Category: 2300 lbs.
Utility Category: 2000 lbs.
Weight in Baggage Compartment, Normal Category:
Baggage Area 1 (or passenger on child's seat) - Station 82 to 108: 120
lbs. See note below.
Baggage Area 2 - Station 108 to 142: 50 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 rear seat must not be occupied.
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight, Skyhawk: 1403 lbs.
Skyhawk II: 1430 lbs.
Maximum Useful Load: Normal Category Utility Category
Skyhawk: 904 lbs. 604 lbs.
Skyhawk II: 877 lbs. 577 lbs.
CABIN AND ENTRY DIMENSIONS
Detailed dimensions of the cabin interior and entry door openings are
illustrated in Section 6.
BAGGAGE SPACE AND ENTRY DIMENSIONS
Dimensions of the baggage area and baggage door opening are
illustrated in detail in Section 6.
SPECIFIC LOADINGS
Wing Loading: 13.2 lbs./sq. ft.
Power Loading: 14.4 Ibs./hP.
1 JuIy 1979 1-5

SECTION 1
GENERAL
SYMBOLS, ABBREVIATIONS AND
TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
KCAS
CESSNA
MODEL 172N
I(nots Calibrated Airspeed is indicated airspeed corrected
for position and instrument error and expressed in knots.
Knots calibrated airspeed is equal to KTAS in standard
atmosphere at sea level.
Knots Indicated Airspeed is the speed shown on the
airspeed indicator and expressed in knots.
Knots True Airspeed is the airspeed expressed in knots
relative to undisturbed air which is KCAS corrected for
altitude and temperature.
Manuevering Speed is the maximum speed at which you
may use abrupt control travel.
Maximum Flap Extended Speed is the highest speed
permissible with wing flaps in a prescribed extended
position.
Maximum Structural Cruising Speed is the speed that
should not be exceeded except in smooth air, then only with
caution.
Never Exceed Speed is the speed limit that may not be
exceeded at any time.
Stalling Speed or ttre 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 configu-
ration at the most forward center of gravity.
Best Angle-of-Climb Speed is the speed which results in
the greatest gain of altitude in a given horizontal distance.
Best Rate-of-Climb Speed is the speed whieh results in the
greatest gain in altitude in a given time.
M ETEORO LOGICAL TER MI NOLOGY
KIAS
KTAS
ve
Vpp
vNo
vrun
Vs
tao
Vx
Vv
OAT
1-6
Outside Air Temperature is the free air statie temperature.
1 JuIy 1979

SECTION 1
GENERAL
It is expressed in either degrees Celsius or degrees Fah-
renheit.
Standard Temperature is 15oC at sea Ievel pressure alti-
tude and decreases by 2"C for each 1000 feet of altitude.
Pressure Altitude is the altitude read from an altimeter
when the altimeter's barometric scale has been set to 29.92
inches of mercury (1013 mb).
ENGINE POWER TERMINOLOGY
CESSNA
MODEL 172N
Standard
Tempera-
ture
Pressure
Altitude
BHP
RPM
Static
RPM
Demon-
strated
Crosswind
Velocity
Usable Fuel
Unusable
Fuel
GPH
NMPG
1 JuIy 1979
AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
Brake I{orsepower is the power developed by the engine.
Revolutions Per Minute is engine speed.
Static RPM is engine speed attained during a full-throttle
engine runup when the airplane is on the ground and
stationary.
Demonstrated Crosswind Velocity is the velocity of the
crosswind component 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 quantity of fuel that can not be safely
used in flight.
Gallons Per Hour is the amount of fuel (in gallons)
consumed per hour.
Nautical Miles Per Gallon is the distance (in nautical
miles) which can be expected per gallon of fuel consumed
at a specific engine power setting and/or flight configura-
tion.
g is acceleration due to gravity.
L-7

1-S/(1-10 blank)
I JuIv 19?9
l
)

CESSNA
MODEL 172N
Maximum
Landing
Weight
Tare
1 JuIy 1979
SECTION 1
GENERAL
Maximum Landing llleight is the maximum weight ap-
proved for the landing touchdown.
Tare is the weight of chocks, blocks, stands, etc. used when
weighing an airplane, and is included in the scale read-
ings. Tare is deducted from the scale reading to obtain the
actual (net) airplane weight.
1-9l(1-10 blank)

CESSNA
MODEL 172N SECTION 2
LIMITATIONS
SECTION 2
LIMITATIONS
TABLE OF CONTENTS Page
Introduction 2-3
Airspeed Limitations 2-4
Airspeed Indicator Markings 2-5
Power Plant Limitations 2-5
Power Plant Instrument Markings 2-6
Weight Limits 2-6
NormaL Category 2-6
Utility Category 2-7
Center Of Gravity Limits 2-7
Normal Category 2-7
Utility Category z:/
Maneuver Limits 2-7
Normal Category 2-7
Utility Category 2-7
Flight Load Factor Limits 2-8
Normal Category 2-8
2-8
2-9
2-9
2-9
2-9
2-ro
Utility Category
1 July 1979 2-ll(2-2 blank)
Kinds Of Operation Limits
Fuel Limitations
Other Limitations
Flap Limitations
Placards

SECTION 2
LIMITATIONS CESSNA
MODEL 172N
1 JuIy 1979
A!RSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown in
figure 2-1. Maneuvering speeds shown apply to normal category opera-
tions. The utility category maneuvering ipeed is 97 KIAS at 2boo pounas.
Figure 2-1. Airspeed Limitations
2-4
SPEED KCAS KIAS R EMAR KS
Vrur Never Exceed Speed 158 158 Do not exceed this speed in
any operation.
Vruo Maximum Structural
Cruising Speed 126 12t Do not exceed this speed
except in smooth air, and
then only with caution.
Maneuvering Speed:
2300 Pounds
1950 Pounds
1600 Pounds
96
B8
80
97
89
80
Do not make full or abrupt
control movements above
this speed.
Vre Maximum Flap Extended
Speed:
lOo Flaps
loo - 40o Flaps 110 87 110
B5 Do not exceed this speed
with flaps down.
Maximum Window Open
Speed 158 158 Do not exceed this speed
with windows open.

INTRODUCTION
section 2 includes operating limitations, instrument markings, and
basic placards necessary for the safe operation of the airplane, its engine,
standard systems and itandard equipment. The limitations included in
this sectioi and in Section t have been approved by the Federal Aviation
Administration. Observance of these operating Iimitations is required by
Federal Aviation Regulations'
NOTE
Refer to Section 9 of this Pilot's Operating Handbook for
amended operating limitations, operating procedures'
performanc-e data ind other necessary information for
iirplanes equipped with specific options'
NOTE
The airspeeds listed in the Airspeed Limitations chart
(figure Z-t) and the Airspeed Indicator Markings chart
ifi[r"" 2-2j are based on Airspeed Calibration data shown
inSection5withthenormalstaticsource.Ifthealternate
static source is being used, ample margins should be
observed to allow forlhe airspeed calibration variations
between the normal and alternate static sources as shown
in Section 5.
Your cessna is certificated under FAA Type certificate No. 3A12 as
Cessna Model No. 172N.
CESSNA
MODEL 172N
1 July 1979
SECTION 2
LIMITATIONS
2-3

CESSNA SECTION 2
MODEL 172N LIMITATIONS
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code significance are
shown in figure 2-2.
Figure 2-2. Airspeed Indicator Markings
POWER PLANT LIMITATIONS
trngine Manufacturer: Avco Lycoming.
Engine Model Number: O-320-H2AD.
nn[lne Operating Limits for Takeoff and Continuous Operations:
Maximum Power: 160 BHP rating.
Maximum Engine SPeed: 2700 RPM'
NOTE
ThestaticRPMrangeatfu]lthrottle(carburetorheatoff
and full rich mixture) is 2280 to 2400 RPM'
Maximum Oil Temperature: 245oF (118'C)'
Oil Pressure, Minimum: 25 Psi'
Maximum: 115 Psi'
Propeller Manufacturer: McCauley Accessory Division'
PropeIIer Model Number: 1C160/DTM7557'
Propelier D iameter' M lf,l#J#' ;f ,11;,l""J.
1 July 1979
MARKING KIAS VALUE
OR RANGE SIGN IFICANCE
White Arc 33-85 Full Flap OPerating Range. Lower
limit is maximum weight V5o in
landing configuration. Upper limit
is maximum sPeed Permissible with
flaps extended.
Green Arc 44 127 Normal Operating Range. Lower limit
is maximum weight Vg at most forward
C.G. with flaps retractad. Upper limit
is maximum structural cruising speed'
Yellow Arc 127 - 158 Operations must be conducted with
caution and onlY in smooth air'
Red Line 158 Maximum sPeed for all oPerations.

SECTION 2
LIMITATIONS CESSNA
MODEL 172N
POWER PLANT INSTRUMENT MARKINGS
Power plant instrument markings and their color code significance
are shown in figure 2-3.
Figure 2-3. Power Plant Instrument Markings
WEIGHT LIMITS
NORMAL CATEGORY
Maximum Ramp Weight: 2307 lbs.
Maximum Takeoff Weight: 2300 lbs.
Maximum Landing Weight: 2300 lbs.
Maximum Weight in Baggage Compartment:
Baggage Area 1 (or passenger on child's seat) - Station 82 to 108: 120
lbs. See note below.
Baggage Area 2 - Station 108 to 142: 50 lbs. See note below.
NOTE
The maximum combined weight capacity for baggage
areas 1 and 2 is 120 lbs.
1 July 1979
2-6
I NSTRUMENT RED LINE GREEN ARC YELLOW ARC RED LINE
MINIMUM
LIMIT NORMAL
OPERATI NG CAUTION RANGE IVIAXIMUM
LIMIT
Tachometer:
Sea Level
5000 Feet
10000 Feet
Oil Temperature
Oil Pressure
Fuel Ouantity
(Standard
Tanks)
Fuel Ouantity
(Long Range
Tanks)
Suction
25 psi
E
(l.5 Gal. Unusable
Each Tank)
E
(2.0 Gal. Unusable
Each Tank)
2100-2450 RPM
2100-2575 RPM
2100-2700 RPM
1000-2450F
60-90 psi
4.5-5.4 in. Hg
27OO RPM
2450F
1 15 psi

CESSNA
MODEL 172N
UTILITY CATEGORY
Maximum Ramp Weight: 2007 lbs.
Maximum Takeoff Weight: 2000 lbs.
Maximum Landing Weight: 2000 lbs.
Maximum Weight in Baggage Compartment:
baggage compartment and rear seat must
SECTION 2
LIMITATIONS
In the utility categorY, the
not be occupied.
CENTER OF GRAVITY LIMITS
NORMAL CATEGORY
Center of GravitY Range:
Forward: 35.0 inch[s aft of datum at 1950 lbs. or less, with straight line
variation to 38.5 inches aft of datum at 2300 lbs'
Prft 47.3 inches aft of datum at aII weights'
Reference Datum: Lower portion of front face of firewall'
UTILITY CATEGORY
Center of GravitY Range:
Forward: SS.b inch6s aft of datum at 1950 lbs. or less, with straight line
variation to 35.5 inches aft of datum at 2000 lbs'
Aft: 40.5 inches aft of datum at aII weights'
Reference Datum: Lower portion of front face of firewall'
MANEUVER LIMITS
NORMAL CATEGORY
This airplane is certificated in both the normal and utility category.
The normal category is applicable to aircraft intended for non-aerobatic
operations. Thei include-any maneuvers incidental to normal flying,
sialls (except whip stalls), lazy eights, chandelles, and turns in which the
angte of banX is.rot *oreihan-60o. Aerobatic maneuvers, including spins,
are not approved.
UTILITY CATEGORY
Thisairplaneisnotdesignedforpurelyaerobaticflight..H,owever,in
the acquisitiol or r"rious ce"rtificateJsuctras commercial pilot and flight
instructor, certain maneuvers are required by the FAA' Al1 of these
maneuvers are permitted in this airplLne when operated in the utility
category.
I JuIy 1979 2-7