Cessna 172S Skyhawk Quick setup guide

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CeSSrii
ATextron Company
• 1725 5kyhawk
Information Manual
172SIM

CESSNA
MODEL 172S
NOTICE
INTRODUCTION
AT THE TIME OF ISSUANCE, THIS INFORMATION
MANUAL WAS AN EXACT DUPLICATE OF THE
OFFICIAL PILOT'S OPERATING HANDBOOK AND
FAA APPROVED AIRPLANE FLIGHT MANUAL AND
IS TO BE USED FOR GENERAL PURPOSES ONLY.
IT WILL NOT BE KEPT CURRENT 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 AIRPLANE.
THE PILOT'S OPERATING HANDBOOK MUST BE
CARRIED IN THE AIRPLANE AND AVAILABLE TO
THE PILOT AT ALL TIMES.
I Revision 5
Cessna Aircraft Company
Original Issue - 8 July 1998
Revision 5 - 19 July 2004
U.S.

INTRODUCTION CESSNA
MODEL 172S
PERFORMANCE -SPECIFICATIONS
*SPEED:
Maximum at Sea Level . . . . . . . . . . . . . . . . . . . . . . . . . 126 KNOTS
Cruise, 75% Power at 8500 Feet. ................. 124 KNOTS
CRUISE: Recommended lean mixture with fuel allowance for engine
start, taxi, takeoff, climb and 45 minutes reserve.
75% Power at 8500 Feet
..................... Range -518 NM
53 Gallons Usable Fuel.
.................... Time -4.26 HRS
Range at 10,000 Feet, 45% Power ............. Range -638 NM
53 Gallons Usable Fuel. .................... Time -6.72 HRS
RATE-OF-CLIMB AT SEA LEVEL ...................... 730 FPM
SERVICE CEILING ............................. 14,000 FEET
TAKEOFF PERFORMANCE:
Ground Roll
.................................... 960 FEET
Total Distance Over 50 Foot Obstacle ............... 1630 FEET
LANDING PERFORMANCE:
Ground Roll
.................................... 575 FEET
Total Distance Over 50 Foot Obstacle ............... 1335 FEET
STALL SPEED:
Flaps Up, Power Off
.............................. 53 KCAS
Flaps Down, Power Off
........................... .48 KCAS
MAXIMUM WEIGHT:
Ramp ..................................... 2558 POUNDS
Takeoff .................................... 2550 POUNDS
Landing ................................... 2550 POUNDS
STANDARD EMPTY WEIGHT .................... 1663 POUNDS
MAXIMUM USEFUL LOAD
....................... 895 POUNDS
BAGGAGE ALLOWANCE ........................ 120 POUNDS
(Continued Next Page)
Iii
U.S. Revision 5

CESSNA
MODEL 172S INTRODUCTION
PERFORMANCE -SPECIFICATIONS (Continued)
WING LOADING: Lbs/Sq. Ft. ............................. 14.7
POWER LOADING: Lbs/HP .............................. 14.2
FUEL CAPACITY
............................... 56 GALLONS
OIL CAPACITY
.................................. 8 QUARTS
ENGINE: Textron Lycoming ......................... IO-360-L2A
180
BHP at 2700 RPM
PROPELLER: Fixed Pitch, Diameter. ................. 76 INCHES
NOTE
*Speed performance is shown for an airplane equipped with
speed fairings which increase the speeds by
approximately 2 knots. There is a corresponding difference
in
range, while all other performance figures are
unchanged when speed fairings are installed.
The above performance figures are based on airplane weights at 2550
pounds, standard atmospheric conditions, level, hard-surfaced dry
runways and
no wind. They are calculated values derived from flight
tests conducted by Cessna Aircraft Company under carefully
documented conditions and will vary with individual airplanes and
numerous factors affecting flight performance.
I Revision 5 U.S. iii/iv

CESSNA
MODEL 172S INTRODUCTION
Information Manual
SKYHAVVK
SP
o Member of GAMA
Cessna Aircraft Company
Model 172S
THIS MANUAL INCORPORATES INFORMATION ISSUED IN THE.
PILOT'S OPERATING HANDBOOK AND FAA APPROVED
AIRPLANE 'FLIGHT MANUAL AT REVISION 5 DATED 19 JULY 2004
(PART NUMBER 172SPHUS05).
COPYRIGHT© 1998
CESSNAAIRCRAFT COMPANY
WICHITA, KANSAS USA
I Revision 5 U.S.
172SIM
v/vi

CESSNA
MODEL 172S INTRODUCTION
TABLE OF CONTENTS
SECTION
GENERAL .............................................. 1
LIMITATIONS ............................................ 2
EMERGENCY PROCEDURES .............................. 3
NORMAL PROCEDURES .................................. 4
PERFORMANCE ......................................... 5
WEIGHT AND BALANCE/EQUIPMENT LIST ................... 6
AIRPLANE AND SYSTEMS DESCRIPTION .................... 7
HANDLING, SERVICE AND MAINTENANCE ................... 8
SUPPLEMENTS ......................................... 9
I Revision 5 U.S. vii/viii

CESSNA
MODEL 172S
SECTION 1
GENERAL
TABLE OF CONTENTS
Three View -Normal Ground Attitude
SECTION 1
GENERAL
Page
1-2
Introduction
...................................... 1-4
Descriptive Data
.................................. 1-4
Engine ....................................... 1-4
Propeller ...................................... 1-4
Fuel
......................................... 1-4
Oil .......................................... 1-5
Maximum Certificated Weights . . . . . . . . . . . . . . . . . . . . . 1-6
Standard Airplane Weights
........................ 1-7
Cabin And Entry Dimensions
....................... 1-7
Baggage Space And Entry Dimensions
............... 1-7
Specific Loadings
............................... 1-7
Symbols, Abbreviations and Terminology
................ 1-8
General Airspeed Terminology And Symbols
........... 1-8
Meteorological Terminology
........................ 1-9
Engine Power Terminology
........................ 1-9
Airplane Performance And Flight Planning Terminology 1-10
Weight And Balance Terminology
.................. 1-11
Metric1Imperial 1U.S. Conversion Charts
.............. 1-13
Weight Conversions
............................ 1-14
Length Conversions ............................ 1-16
Distance Conversions
........................... 1-20
Volume Conversions
............................ 1-21
Temperature Conversions ........................ 1-24
Hectopascals
~o Inches Me.rcury ................... 1-251
Volume to Weight Conversions .................... 1-26
Quick Conversions
......................... 1-27/1-28
Revision 4
1-1

SECTION 1
GENERAL CESSNA
MODEL 172S
It-· ---36'-1"--~'1
76" MAX
~ Figure 1-1. Three View -Normal Ground
Attitude (Sheet 1 of
2)
0510T1005
051 OT1 005
1-2 Revision 4

CESSNA
MODEL 172S SECTION 1
GENERAL
~------~27'-2" -------~
NOTE 1: WING SPAN SHOWN WITH STROBE LIGHTS
INSTALLED.
NOTE 2: WHEEL BASE LENGTH IS 65".
NOTE 3: PROPELLER GROUND CLEARANCE IS 11 1/4".
NOTE 4: WING AREA IS 174 SQUARE FEET.
NOTE 5: MINIMUM TURNING RADIUS (* PIVOT POINT TO
OUTBOARD WING TIP)
IS 27'-51/2".
NOTE 6: NORMAL GROUND ATTITUDE IS SHOWN WITH
NOSE STRUT SHOWING APPROXIMATELY 2" OF
STRUT, AND WINGS LEVEL.
__ Figure 1-1. Three View -Normal Ground
Attitude (Sheet 2)
051 OT1 005
Revision 4 1-3

SECTION 1
GENERAL
INTRODUCTION
CESSNA
MODEL 172S
I This handbook contains 9 sections, and includes the material
required to be furnished to the pilot by FAR Part 23. It also contains
Isupplemental 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: Textron Lycoming.
Engine Model Number: IO-360-L2A.
Engine Type: Normally aspirated, direct drive, air-cooled,
horizontally opposed, fuel injected, four cylinder
engine with 360 cu. in. displacement.
Horsepower Rating and Engine Speed: 180 rated BHP
at 2700 RPM.
PROPELLER
Propeller Manufacturer: McCauley Propeller Systems.
Propeller Model Number: 1A170E/JHA7660.
Number of Blades: 2.
Propeller Diameter: 76 inches.
Propeller Type: Fixed pitch.
FUEL A WARNING
USE OF UNAPPROVED FUELS MAY RESULT IN
DAMAGE TO THE ENGINE AND FUEL SYSTEM
COMPONENTS, RESULTING
IN POSSIBLE
ENGINE FAILURE.
Approved Fuel Grades (and Colors):
1-4
1 OOLL Grade Aviation Fuel (Blue).
100 Grade Aviation Fuel (Green).
Revision 4

CESSNA
MODEL 172S SECTION 1 GENERAL
NOTE
Isopropyl alcohol or diethylene glycol mono methyl ether
(DiEGME)
may be added to the fuel supply. Additive
concentrations shall not exceed 1% for isopropyl alcohol or
0.10% to 0.15% for DiEGME. Refer to Section 8 for
additional information.
Fuel Capacity:
Total Capacity: 56.0
U.S. gallons.
53.0
U.S. gallons.
Total Usable:
Total Capacity
Each Tank: 28.0 U.S. gallons.
Total Usable
Each Tank: 26.5 U.S. gallons.
OIL
NOTE
To ensure maximum fuel capacity and minimize cross-
feeding
when refueling, always park the airplane in a wings-
level, normal ground attitude and place the fuel selector in
the Left or Right position. Refer to Figure 1-1 for normal
ground attitude dimensions.
Oil Specification:
MIL-L-6082 or SAE J1966 Aviation Grade Straight Mineral Oil:.
Used when the airplane was delivered from the factory and should
be used to replenish the supply during the first 25 hours. This oil
should
be drained and the filter changed after the first 25 hours of
operation. Refill
the engine with MIL-L-6082 or SAE J1966 Aviation.
Grade Straight Mineral
Oil and continue to use until a total of 50
hours has accumulated or oil consumption has stabilized.
MIL-L-22851 or SAE J1899 Aviation Grade Ashless Dispersantl
Oil:
Oil conforming to the latest revision and/or supplements to
Textron Lycoming Service Instruction No.1
014, must be used after
first
50 hours or once oil consumption has stabilized.
Revision 4 1-5

SECTION 1
GENERAL CESSNA
MODEL 172S
Recommended Viscosity for Temperature Range:
ITemperature MIL-L-6082 MIL-L-22851 or SAE
or J1899
SAE J1966 Ashless Dispersant
Straight SAE Grade
Mineral Oil
SAE Grade
Above 27°C (80°F)
60
1SW-SO, 20W-SO or 60
Above 16°C (60°F)
SO
40 or SO
-1°C (30°F) to 32°C (gO°F)
40 40
-18°C (0° F) to 21 °c (70°F)
30
30, 40 or 20W-40
Below -12°C (10°F)
20 30 or 20W-30
-18°C (O°F) to 32°C (gO°F) 20W-SO 20W-SO
or 1SW-SO
All Temperatures
---
1SW-SO or 20W-SO
NOTE
When operating temperatures overlap, use the lighter
grade of oil.
Oil Capacity:
Sump: 8 U.S. Quarts
I Total: 9 U.S. Quarts
MAXIMUM CERTIFICATED WEIGHTS
Ramp Weight Normal Category:
Utility Category:
Takeoff Weight Normal Category:
Utility Category:
Landing Weight Normal Category:
Utility Category:
1-6
25581bs.
22081bs.
25501bs.
22001bs.
25501bs.
22001bs.
Revision 4

CESSNA
MODEL 172S SECTION 1
GENERAL
Weight
in Baggage Compartment, Normal Category:
Baggage Area 1 (Station 82 to 108): 120 Ibs. See note below.
Baggage Area 2 (Station 108 to 142): 50 Ibs. See note below.
NOTE
The maximum combined weight capacity for Baggage Area
1 and Baggage Area 2 is 120 Ibs.
Weight in Baggage Compartment, Utility Category:
In this category, the rear seat must not be occupied and the
baggage compartment must be empty.
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight:
Maximum Useful Load, Normal Category
Maximum Useful Load, Utility Category:
CABIN AND ENTRY DIMENSIONS
16631bs.
8951bs.
5451bs.
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:
Power Loading: 14.7Ibs./sq. ft. 14.2 Ibs'/hp.
I
Revision 4 1-7

SECTION 1
GENERAL CESSNA
MODEL 172S
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
KCAS
KIAS
KTAS
Vs
Vso
Vx
Vy
Knots Calibrated Airspeed is indicated airspeed
corrected for position
and instrument error and
expressed in knots. Knots calibrated airspeed is equal
to KT AS 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.
Maneuvering Speed
is the maximum speed at
which
full or abrupt control movements may be used
without overstressing the airframe.
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 the minimum steady flight
speed is the minimum speed at which the airplane is
controllable.
Stalling Speed
or the minimum steady flight
speed is the minimum speed at which the airplane is
controllable in the landing configuration 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 which
results in the greatest gain in altitude in a given time.
Revision 4

CESSNA
MODEL 172S SECTION 1
GENERAL
METEOROLOGICAL TERMINOLOGY
OAT
Standard
Temperature
Outside Air Temperature is the free air static
temperature.
It may be expressed in either degrees
Celsius or degrees Fahrenheit.
Standard Temperature is 15°C at sea level
pressure altitude and decreases by 2°C for each
1000 feet of altitude.
Pressure Pressure Altitude is the altitude read from an
Altitude altimeter when the altimeter's barometric scale has
been set to 29.92 inches of mercury (1013
mb).
ENGINE POWER TERMINOLOGY
BHP
RPM
Static
RPM
MAP
Lean
Mixture
Rich
Mixture
Full Rich
Idle Cutoff
Revision 4
Brake Horsepower 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.
Manifold Absolute Pressure is the absolute
pressure measured in the engine induction system.
MAP
is measured in units of inches of mercury
(inHG).
Decreased proportion of fuel
in the fuel-air mixture
supplied to the engine. As air density decreases,
the amount
of fuel required by the engine decreases
for a given throttle setting. Adjusting the fuel-air
mixture to provide a smaller portion of fuel is known
as "leaning" the mixture.
Increased proportion of fuel in the fuel-air mixture
supplied to the engine. As air density increases, the
amount of fuel required by the engine increases for
a given throttle setting. Adjusting the fuel-air mixture
to provide a greater portion
of fuel is known as
"richening" the mixture.
Mixture control full forward (pushed in, full control
travel, toward the panel).
Mixture control full aft (pulled out, full control travel,
away from the panel).

SECTION 1
GENERAL CESSNA
MODEL 172S
ENGINE POWER TERMINOLOGY (Continued)
Full
Throttle
Closed
Throttle
Throttle full forward (pushed in, full control travel,
toward the panel) Also known as "full open" throttle.
Throttle full aft (pulled out, full control travel, away
from the panel). Also known as the throttle "idle"
position.
AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
Demon-
strated
Crosswind
Velocity
Usable Fuel
Unusable
Fuel
GPH
NMPG
g
Course
Datum
1-10
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 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 consumed
per hour.
Nautical Miles Per Gallon is the distance which can
be expected per gallon of fuel consumed at a
specific engine power setting and/or flight
configuration.
9 is acceleration due to gravity.
Course Datum is the compass reference used by
the autopilot, along with course deviation, to provide
lateral control when tracking a navigation signal.
Revision 4

CESSNA
MODEL 172S SECTION 1
GENERAL
WEIGHT AND BALANCE TERMINOLOGY
Reference
Datum
Station
Arm
Moment
Center of
Gravity
(C.G.)
C.G.
Arm
C.G.
Limits
Standard
Empty
Weight
Reference Datum is an imaginary vertical plane from
which all horizontal distances are measured for
balance purposes.
Station is a location along the airplane fuselage given
in terms of the distance from the reference datum.
Arm is the horizontal distance from the reference
datum to the center of gravity (C.G.) of
an item.
Moment is the product of the weight of an item
multiplied by its arm. (Moment divided
by the constant
1000 is used in this handbook to simplify balance
calculations by reducing the number of digits.)
Center of Gravity is the point at which an airplane, or
equipment, would balance if suspended. Its distance
from the reference datum is found by dividing the
total moment by the total weight of the airplane.
Center of Gravity Arm is the arm obtained by
adding the airplane's individual moments and dividing
the sum
by the total weight.
Center of Gravity Limits are the extreme center of
gravity locations within which the airplane must be
operated at a given weight.
Standard Empty Weight is the weight of a standard
airplane, including unusable fuel, full operating fluids
and full engine oil.
Basic Empty Basic Empty Weight is the standard empty weight
Weight plus the weight of optional equipment.
Useful Load Useful Load
is the difference between ramp weight
and the basic empty weight.
MAC
July 8/98
MAC (Mean Aerodynamic Chord) is the chord of an
imaginary rectangular airfoil having the same pitching
moments throughout the flight range as that of the
actual wing.
1-11