Cessna 172S Nav III Quick setup guide

Cessna
i
172SNAV
SKYHAWK
SP
Information Manual
_
172SIMAUS
Model 172S
Nav III Avionics
Serials 172S9810and On

CESSNA . INTRODUCTION
MODEL 172SNAV III
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 PILOTS
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
Revision 3 U.S.

INTRODUCTION CESSNA —
MODEL 172SNAV III
PERFORMANCE - SPECIFICATIONS _
*SPEED: —
Maximum at Sea Level 126 KNOTS
Cruise, 75% Power at 8500 Feet 124 KNOTS
i—
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)
—
n
U.S. Revision 3 —
n

CESSNA INTRODUCTION
MODEL 172SNAV III
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
180BHPat2700RPM
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.
Revision 3 U.S. iii/iv

CESSNA INTRODUCTION
MODEL 172SNAVII1
Cessna
A Tejttron Company
Information Manual
SK^H/WVK
Member □( GAMA
Cessna Aircraft Company
Model 172S
NAV III AVIONICS OPTION
Serials 172S9810and 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
Revision 3 U.S. v/vi

CESSNA INTRODUCTION
MODEL 172SNAV III
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
Revision 3 U.S. vii/viii

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

SECTION 1
GENERAL
CESSNA
MODEL 172SNAV III
NOTE
• Wing span is shown with strobe lights installed.
• Wheel base length is 65".
• Propeller ground clearance is 11 1/4".
• Wing area is 174 square feet.
• Minimum turning radius (* pivot point to outboard
wing tip) is 27'-5 1/2".
• 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)
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
MODEL 172SNAV
SECTION 1
GENERAL
OIL (Continued)
Recommended Viscosity for Temperature Range:
Temperature
Above 27QC (80DF)
Above 16°C(60°F)
-1°C(30°F)to32°C(90QF)
-18oC(0°F)to21°C(70oF)
Below -12°C{10°F)
-18°C(0°F)to32°C (90°F)
All Temperatures
MIL-L-6082
or
SAEJ1966
Straight
Mineral Oil
SAE Grade
60
50
40
30
20
20W-50
—
MIL-L-22851 or SAE
J1899
Ashless Dispersant
SAE Grade
15W-50, 20W-50or60
40 or 50
40
30, 40 or 20W-40
30 or 20W-30
20W-50or15W-50
15W-50or20W-50
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
Takeoff Weight
Landing Weight
Normal Category; 2558 lbs.
Utility Category: 2208 lbs.
Normal Category: 2550 lbs.
Utility Category: 2200 lbs.
Normal Category: 2550 lbs.
Utility Category: 2200 lbs.
(Continued Next Page)
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 (or
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 Ibs./sq. ft.
Power Loading: 14.2lbs./hp. —
-
1-8 U.S. 172SPHAUS-00

CESSNA
MODEL 172SNAV
SECTION 1
GENERAL
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
KCAS
KIAS
KTAS
_
Vs0
Vy
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.
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-C!imb Speed is the speed which results
in the greatest gain in altitude in a given time.
172SPHAUS-00
U.S. 1-9
^

~
SECTION 1
GENERAL
CESSNA
MODEL 172SNAV III
METEOROLOGICAL TERMINOLOGY
OAT
Standard
Temperature
Pressure
Altitude
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
1000 feet of altitude.
each
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
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
MODEL 172SNAV
SECTION 1
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.
g g is 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
GENERAL
CESSNA
MODEL 172SNAV 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

CESSNA
MODEL 172SNAV
SECTION 1
GENERAL
WEIGHT AND BALANCE TERMINOLOGY (Continued)
_
MAC
Maximum
Ramp
Weight
Maximum
Takeoff
Weight
Maximum
Landing
Weight
Tare
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.
Maximum Ramp Weight is the maximum weight
approved for ground maneuver, and includes the
weight of fuel used for start, taxi and runup.
Maximum Takeoff Weight is the maximum weight
approved for the start of the takeoff roll.
Maximum Landing Weight is the maximum weight
approved for the landing touchdown.
Tare is the weight of chocks, blocks, stands, etc.
used when weighing an airplane, and is included in
the scale readings. Tare is deducted from the scale
reading to obtain the actual (net) airplane weight.
_
172SPHAUS-00
U.S. 1-13

SECTION 1 CESSNA
GENERAL MODEL 172S NAV III
METRIC / IMPERIAL / U.S. CONVERSION CHARTS
The following charts have been provided to help international
operators convert U.S. measurement supplied with the Pilot's
Operating Handbook into metric and imperial measurements.
The standard followed for measurement units shown, is the National
Institute of Standards Technology (NIST), Publication 811, "Guide
for the Use of the International System of Units (SI)."
Refer to the following pages for these charts.
1-14 U.S. 172SPHAUS-00

CESSNA
MODEL 172SNAV
SECTION 1
GENERAL
(Kilograms x 2.205 = Pounds) (Pounds x .454 = Kilograms)
KILOGRAMS INTO POUNDS
KILOGRAMMES EN LIVRES
kg
0
10
20
30
40
50
60
70
80
90
100
0
Ib.
22.046
44.093
66.139
88.185
110.23
132.28
154.32
176.37
198.42
220.46
1
Ib.
2.205
24.251
46.297
68.343
90.390
112.44
134.48
156.53
178.57
200.62
222.67
2
Ib.
4.409
26.456
48.502
70.548
92.594
114.64
136.69
158.73
180.78
202.83
224.87
3
Ib.
6.614
28.660
50.706
72.753
94.799
116.85
138.89
160.94
182.98
205.03
227.08
4
Ib.
8.819
30.865
52.911
74.957
97.003
119.05
141.10
163.14
185.19
207.24
229.28
5
ib
11.023
33.069
55.116
77.162
99.208
121.25
143.30
165.35
187.39
209.44
231.49
6
ib
13 226
35.274
57.320
79.366
101.41
123.46
145.51
167.55
189.60
211.64
233.69
7
Ib.
15.432
37.479
59.525
81.571
103.62
125.66
147.71
169.76
191.80
213.85
235.90
8
Id
17.637
39.683
61.729
83.776
105.82
127.87
149.91
171.96
194.01
216.05
238 10
9
ib
19.842
41.888
63.934
85.980
108.03
130.07
152.12
174.17
196.21
218.26
240.30
POUNDS INTO KILOGRAMS
LIVRES EN KILOGRAMMES
Ib.
0
10
20
30
40
SO
60
70
80
90
100
0
kg
4.536
9.072
13.608
18.144
22.680
27.216
31.752
36.287
40.823
45.359
1
kg
0.454
4.990
9.525
14.061
18.597
23.133
27.669
32.205
36.741
41.277
45.813
2
kg
0.907
5.443
9.979
14.515
19.051
23.587
28.123
32.659
37.195
41.731
46.266
3
kg
1 361
5.897
10.433
14.969
19.504
24.040
28.576
33.112
37.648
42.184
46 720
4
kg
1.814
6.350
10.886
15.422
19.958
24.494
29.030
33.566
38.102
42.638
47.174
5
kg
2.268
6.804
11.340
15.876
20.412
24.948
29.484
34.019
38.555
43.091
47 627
6
kg
2.722
7.257
11.793
16.329
20.865
25.401
29.937
34.473
39.009
43.545
48.081
7
kg
-: 175
7.711
12.247
16.783
21.319
25.855
30.391
34.927
39.463
43.999
48.534
8
kg
3.629
8.165
12.701
17.237
21.772
26.303
30.844
35.380
39.916
44.452
48.988
9
kg
4.082
8.616
13.154
17.690
22.226
26.762
31.298
35.834
40.370
44.906
49.442
Figure 1-2. Weight Conversions (Sheet 1 of 2)
172SPHAUS-00
U.S. 1-15