Cessna 172S Skyhawk SP NAV III 2005 Quick setup guide

CESSNA INTRODUCTION
MODEL 172S NAV III
U.S.
NOTICE
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.
Cessna Aircraft Company
Original Issue - 25 February 2005
Revision 3 - 12 October 2006
iRevision 3

INTRODUCTION CESSNA
MODEL 172S NAV III
U.S.
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 HOURS
Range at 10,000 Feet, 45% Power. . . . . . . . . . . . . Range - 638 NM
53 Gallons Usable Fuel . . . . . . . . . . . . . . . . . . Time - 6.72 HOURS
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
(Continued Next Page)
Revision 3
ii

CESSNA INTRODUCTION
MODEL 172S NAV III
U.S.
PERFORMANCE - SPECIFICATIONS (Continued)
STANDARD EMPTY WEIGHT. . . . . . . . . . . . . . . . . . . . 1663 POUNDS
MAXIMUM USEFUL LOAD . . . . . . . . . . . . . . . . . . . . . . . 895 POUNDS
BAGGAGE ALLOWANCE . . . . . . . . . . . . . . . . . . . . . . . . 120 POUNDS
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.
iii/ivRevision 3

CESSNA INTRODUCTION
MODEL 172S NAV III
U.S. v/viRevision 3
Cessna Aircraft Company
Model 172S
NAV III AVIONICS OPTION
Serials 172S9810 and On
THIS MANUAL INCORPORATES INFORMATION ISSUED IN THE
PILOT'S OPERATING HANDBOOK AND FAA APPROVED
AIRPLANE FLIGHT MANUAL AT REVISION 4 DATED 12 OCTOBER
2006 (PART NUMBER 172SPHAUS-04).
COPYRIGHT © 2005
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS USA 172SIMAUS-03

CESSNA INTRODUCTION
MODEL 172S NAV III
U.S.
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
vii/viiiRevision 3

CESSNA SECTION 1
MODEL 172S NAV III GENERAL
GENERAL
TABLE OF CONTENTS
Page
Three View - Normal Ground Attitude . . . . . . . . . . . . . . . . . . . 1-3
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5
Descriptive Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5
Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5
Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5
Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5
Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6
Maximum Certificated Weights . . . . . . . . . . . . . . . . . . . . . 1-7
Standard Airplane Weights . . . . . . . . . . . . . . . . . . . . . . . . 1-8
Cabin And Entry Dimensions . . . . . . . . . . . . . . . . . . . . . . . 1-8
Baggage Space And Entry Dimensions . . . . . . . . . . . . . . . 1-8
Specific Loadings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-8
Symbols, Abbreviations and Terminology . . . . . . . . . . . . . . . . 1-9
General Airspeed Terminology And Symbols . . . . . . . . . . . 1-9
Meteorological Terminology . . . . . . . . . . . . . . . . . . . . . . . 1-10
Engine Power Terminology . . . . . . . . . . . . . . . . . . . . . . . 1-10
Airplane Performance And Flight Planning Terminology . . 1-11
Weight And Balance Terminology . . . . . . . . . . . . . . . . . . 1-12
Metric / Imperial / U.S. Conversion Charts . . . . . . . . . . . . . . 1-14
Weight Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-15
Length Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-17
Distance Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21
Volume Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-22
Temperature Conversions . . . . . . . . . . . . . . . . . . . . . . . . 1-25
Hectopascals to Inches Mercury . . . . . . . . . . . . . . . . . . . 1-26
Volume to Weight Conversions . . . . . . . . . . . . . . . . . . . . 1-27
Quick Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-28
172SPHAUS-00 U.S. 1-1/1-2

CESSNA SECTION 1
MODEL 172S NAV III GENERAL
Figure 1-1. Three View - Normal Ground Attitude (Sheet 1 of 2)
172SPHAUS-00 U.S. 1-3

SECTION 1 CESSNA
GENERAL MODEL 172S NAV III
Figure 1-1. Three View - Normal Ground Attitude (Sheet 2)
NOTE
f Wing span is shown with strobe lights installed.
f Wheel base length is 65”.
f Propeller ground clearance is 11 1/4”.
f Wing area is 174 square feet.
f Minimum turning radius (* pivot point to outboard
wing tip) is 27’-5 1/2”.
f Normal ground attitude is shown with nose strut
showing approximately 2” of strut, and wings
level.
1-4 U.S. 172SPHAUS-00

CESSNA SECTION 1
MODEL 172S NAV III GENERAL
INTRODUCTION
This handbook contains 9 sections, and includes the material
required to be furnished to the pilot by FAR Part 23. 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: 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 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):
100LL Grade Aviation Fuel (Blue).
100 Grade Aviation Fuel (Green).
(Continued Next Page)
172SPHAUS-00 U.S. 1-5

SECTION 1 CESSNA
GENERAL MODEL 172S NAV III
FUEL (Continued) NOTE
Isopropyl alcohol or diethylene glycol monomethyl
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.
Total Usable: 53.0 U.S. gallons.
Total Capacity Each Tank: 28.0 U.S. gallons.
Total Usable Each Tank: 26.5 U.S. gallons.
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
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 Dispersant Oil:
Oil conforming to the latest revision and/or supplements to Textron
Lycoming Service Instruction No. 1014, must be used after first 50
hours or once oil consumption has stabilized.
(Continued Next Page)
1-6 U.S. 172SPHAUS-00

CESSNA SECTION 1
MODEL 172S NAV III GENERAL
OIL (Continued)
Recommended Viscosity for Temperature Range:
NOTE
When operating temperatures overlap, use the lighter
grade of oil.
Oil Capacity:
Sump: 8 U.S. Quarts
Total: 9 U.S. Quarts
MAXIMUM CERTIFICATED WEIGHTS
Ramp Weight Normal Category: 2558 lbs.
Utility Category: 2208 lbs.
Takeoff Weight Normal Category: 2550 lbs.
Utility Category: 2200 lbs.
Landing Weight Normal Category: 2550 lbs.
Utility Category: 2200 lbs.
(Continued Next Page)
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                                                                                                            
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Temperature MIL-L-6082
or
SAE J1966
Straight
Mineral Oil
SAE Grade
MIL-L-22851 or SAE
J1899
Ashless Dispersant
SAE Grade
Above 27°C (80°F) 60 15W-50, 20W-50 or 60
Above 16°C (60°F) 50 40 or 50
-1°C (30°F) to 32°C (90°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 (0°F) to 32°C (90°F) 20W-50 20W-50 or 15W-50
All Temperatures
>>> 15W-50 or 20W-50
172SPHAUS-00 U.S. 1-7

SECTION 1 CESSNA
GENERAL MODEL 172S NAV III
MAXIMUM CERTIFICATED WEIGHTS (Continued)
Weight in Baggage Compartment, Normal Category:
Baggage Area 1 (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 Area 1 and Baggage Area 2 is 120 lbs.
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: 1663 lbs.
Maximum Useful Load, Normal Category 895 lbs.
Maximum Useful Load, Utility Category: 545 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: 14.7 lbs./sq. ft.
Power Loading: 14.2 lbs./hp.
1-8 U.S. 172SPHAUS-00

CESSNA SECTION 1
MODEL 172S NAV III GENERAL
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
KCAS Knots 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.
KIAS Knots Indicated Airspeed is the speed shown on the
airspeed indicator and expressed in knots.
KTAS Knots True Airspeed is the airspeed expressed in
knots relative to undisturbed air which is KCAS
corrected for altitude and temperature.
V
A
Maneuvering Speed is the maximum speed at which
full or abrupt control movements may be used without
overstressing the airframe.
V
FE
Maximum Flap Extended Speed is the highest
speed permissible with wing flaps in a prescribed
extended position.
V
NO
Maximum Structural Cruising Speed is the speed
that should not be exceeded except in smooth air,
then only with caution.
V
NE
Never Exceed Speed is the speed limit that may not
be exceeded at any time.
V
S
Stalling Speed or the minimum steady flight speed
is the minimum speed at which the airplane is
controllable.
V
SO
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.
V
X
Best Angle-of-Climb Speed is the speed which
results in the greatest gain of altitude in a given
horizontal distance.
V
Y
Best Rate-of-Climb Speed is the speed which results
in the greatest gain in altitude in a given time.
172SPHAUS-00 U.S. 1-9

SECTION 1 CESSNA
GENERAL MODEL 172S NAV III
METEOROLOGICAL TERMINOLOGY
OAT Outside Air Temperature is the free air static
temperature. It may be expressed in either degrees
Celsius or degrees Fahrenheit.
Standard Standard Temperature is 15°C at sea level
Temperature 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 Brake Horsepower is the power developed by the
engine.
RPM Revolutions Per Minute is engine speed.
Static Static RPM is engine speed attained during a full
RPM throttle engine runup when the airplane is on the
ground and stationary.
MAP Manifold Absolute Pressure is the absolute
pressure measured in the engine induction system.
MAP is measured in units of inches of mercury
(inHG).
Lean Decreased proportion of fuel in the fuel-air mixture
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.
Rich Increased proportion of fuel in the fuel-air mixture
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.
(Continued Next Page)
1-10 U.S. 172SPHAUS-00

CESSNA SECTION 1
MODEL 172S NAV III GENERAL
ENGINE POWER TERMINOLOGY (Continued)
Full Rich Mixture control full forward (pushed in, full control
travel, toward the panel).
Idle Cutoff Mixture control full aft (pulled out, full control travel,
away from the panel).
Full Throttle full forward (pushed in, full control travel,
Throttle toward the panel) Also known as "full open" throttle.
Closed Throttle full aft (pulled out, full control travel, away
Throttle from the panel). Also known as the throttle "idle"
position.
AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
Demon- Demonstrated Crosswind Velocity is the velocity
strated of the crosswind component for which adequate
Crosswind control of the airplane during takeoff and landing
Velocity was actually demonstrated during certification tests.
The value shown is not considered to be limiting.
Usable Fuel Usable Fuel is the fuel available for flight planning.
Unusable Unusable Fuel is the quantity of fuel that can not be
Fuel safely used in flight.
GPH Gallons Per Hour is the amount of fuel consumed
per hour.
NMPG 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.
ggis acceleration due to gravity.
Course Course Datum is the compass reference used by
Datum the autopilot, along with course deviation, to provide
lateral control when tracking a navigation signal.
172SPHAUS-00 U.S. 1-11

SECTION 1 CESSNA
GENERAL MODEL 172S NAV III
WEIGHT AND BALANCE TERMINOLOGY
Reference Reference Datum is an imaginary vertical plane from
Datum which all horizontal distances are measured for
balance purposes.
Station Station is a location along the airplane fuselage given
in terms of the distance from the reference datum.
Arm Arm is the horizontal distance from the reference
datum to the center of gravity (C.G.) of an item.
Moment 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 Center of Gravity is the point at which an airplane, or
Gravity equipment, would balance if suspended. Its distance
(C.G.) from the reference datum is found by dividing the
total moment by the total weight of the airplane.
C.G. Center of Gravity Arm is the arm obtained by
Arm adding the airplane's individual moments and dividing
the sum by the total weight.
C.G. Center of Gravity Limits are the extreme center of
Limits gravity locations within which the airplane must be
operated at a given weight.
Standard Standard Empty Weight is the weight of a standard
Empty airplane, including unusable fuel, full operating fluids
Weight 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.
(Continued Next Page)
1-12 U.S. 172SPHAUS-00