Redarc | R-12-700S | Specifications | Redarc R-12-700S Specifications

CESSNA
MODEL 172R NAV III
GFC 700 AFCS
INTRODUCTION
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 - 20 December 2007
Original Issue
U.S.
i
INTRODUCTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PERFORMANCE - SPECIFICATIONS
*SPEED:
Maximum at Sea Level . . . . . . . . . . . . . . . . . . . . . . . . . 123 KNOTS
Cruise, 75% Power at 8500 Feet. . . . . . . . . . . . . . . . . . 122 KNOTS
CRUISE: Recommended lean mixture with fuel allowance for engine
start, taxi, takeoff, climb and 45 minutes reserve.
80% Power at 8500 Feet . . . . . . . . . . . . . . . . . . . . . Range - 586 NM
53 Gallons Usable Fuel . . . . . . . . . . . . . . . . . . . Time - 4.9 HOURS
Range, 60% Power at 10,000 Feet . . . . . . . . . . . . . Range - 687 NM
53 Gallons Usable Fuel . . . . . . . . . . . . . . . . . . . Time - 6.5 HOURS
RATE OF CLIMB AT SEA LEVEL . . . . . . . . . . . . . . . . . . . . . . 720 FPM
SERVICE CEILING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13,500 FEET
TAKEOFF PERFORMANCE:
Ground Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 945 FEET
Total Distance Over 50 Foot Obstacle . . . . . . . . . . . . . . . 1685 FEET
LANDING PERFORMANCE:
Ground Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 550 FEET
Total Distance Over 50 Foot Obstacle . . . . . . . . . . . . . . . 1295 FEET
STALL SPEED:
Flaps UP, Power Idle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .51 KCAS
Flaps FULL, Power Idle . . . . . . . . . . . . . . . . . . . . . . . . . . . .47 KCAS
MAXIMUM WEIGHT:
Ramp . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2457 POUNDS
Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2450 POUNDS
Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2450 POUNDS
(Continued Next Page)
ii
U.S.
Original Issue
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
INTRODUCTION
PERFORMANCE - SPECIFICATIONS (Continued)
STANDARD EMPTY WEIGHT. . . . . . . . . . . . . . . . . . . . 1639 POUNDS
MAXIMUM USEFUL LOAD . . . . . . . . . . . . . . . . . . . . . . . 818 POUNDS
BAGGAGE ALLOWANCE . . . . . . . . . . . . . . . . . . . . . . . . 120 POUNDS
WING LOADING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1 lbs/sq. ft.
POWER LOADING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3 lbs/HP
FUEL CAPACITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56 GALLONS
OIL CAPACITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 QUARTS
ENGINE: Textron Lycoming . . . . . . . . . . . . . . . . . . . . . . . . . IO-360-L2A
160 BHP at 2400 RPM
PROPELLER:
Fixed Pitch, Diameter . . . . . . . . . . . . . . . . . . . . . . . . . . . 75 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 perf ormance figures are
unchanged when speed fairings are installed.
The above performance figures are based on airplane weights at 2450
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.
Original Issue
U.S.
iii/iv
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
INTRODUCTION
Cessna Aircraft Company
Model 172R
NAV III AVIONICS OPTION - GFC 700 AFCS
Serials 17281497 and On
THIS MANUAL INCORPORATES INFORMATION ISSUED IN THE
PILOT'S OPERATING HANDBOOK AND FAA APPROVED
AIRPLANE FLIGHT MANUAL AT ORIGINAL ISSUE, DATED 20
DECEMBER 2007 (PART NUMBER 172RPHBUS-00).
COPYRIGHT © 2007
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS USA
Original Issue
172RIMBUS-00
U.S.
v/vi
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
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
Original Issue
U.S.
vii/viii
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6
Fuel Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6
Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7
Oil Specification. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7
Oil Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7
Maximum Certificated Weights . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-8
Weight In Baggage Compartment - Normal Category. . . . . . . . . . 1-8
Weight In Baggage Compartment - Utility Category . . . . . . . . . . . 1-8
Standard Airplane Weights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9
Cabin And Entry Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9
Baggage Space And Entry Dimensions . . . . . . . . . . . . . . . . . . . . 1-9
Specific Loadings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-9
Symbols, Abbreviations And Terminology . . . . . . . . . . . . . . . . . . . . 1-10
General Airspeed Terminology And Symbols . . . . . . . . . . . . . . . 1-10
Meteorological Terminology . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11
Engine Power Terminology . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11
Airplane Performance And Flight Planning Terminology . . . . . . . 1-13
Weight And Balance Terminology . . . . . . . . . . . . . . . . . . . . . . . . 1-14
Metric/Imperial/U.S. Conversion Charts. . . . . . . . . . . . . . . . . . . . . . 1-16
Weight Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-17
Length Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-19
Distance Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-23
Volume Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-24
Temperature Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-27
Pressure Conversion. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-28
Volume To Weight Conversion . . . . . . . . . . . . . . . . . . . . . . . . . . 1-29
Quick Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-30
172RPHBUS-00
U.S.
1-1/1-2
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
THREE VIEW - NORMAL GROUND ATTITUDE
Figure 1-1 (Sheet 1 of 2)
172RPHBUS-00
U.S.
1-3
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
THREE VIEW - NORMAL GROUND ATTITUDE
NOTE
•
•
•
•
•
Wing span shown with standard strobe lights installed.
•
Normal ground attitude is shown with nose strut showing
approximately 2 inches of strut, and wings level.
Wheel base length is 65.0 inches.
Propeller ground clearance is 11.25 inches.
Wing area is 174.0 square feet.
Minimum turning radius (*pivot point to outboard wing
tip) is 27.0 feet, 5.50 inches.
Figure 1-1 (Sheet 2)
1-4
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
INTRODUCTION
This POH contains 9 sections, and includes the material required to be
furnished to the pilot by 14 CFR 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 360.0 cu.
in. displacement.
Horsepower Rating and Engine Speed: 160 rated BHP at 2400 RPM
PROPELLER
Propeller Manufacturer: McCauley Propeller Systems
Propeller Model Number: 1C235/LFA7570
Number of Blades: 2
Propeller Diameter: 75 inches
Propeller Type: Fixed pitch
(Continued Next Page)
172RPHBUS-00
U.S.
1-5
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
DESCRIPTIVE DATA (Continued)
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)
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 e n s u r e m a x i m u m f u e l c a p a c i t y a n d m i n i m i z e
crossfeeding 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.
(Continued Next Page)
1-6
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
DESCRIPTIVE DATA (Continued)
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 Textron Lycoming Service Instruction No 1014, and all
revisions and supplements thereto, must be used after first 50 hours
or oil consumption has stabilized.
Recommended viscosity for temperature range:
Temperature
Above 27°C (80°F)
Above 16°C (60°F)
-1°C (30°F) to 32°C (90°F)
-18°C (0°F) to 21°C (70°F)
Below -12°C (10°F)
-18°C (0°F) to 32°C (90°F)
All Temperatures
MIL-L-6082
MIL-L-22851
or SAE J1966
or SAE J1899
Straight Mineral Oil Ashless Dispersant Oil
SAE Grade
SAE Grade
60
50
40
30
20
20W-50
---
60
40 or 50
40
30, 40 or 20W-40
30 or 20W-30
20W-50 or 15W-50
15W-50 or 20W-50
NOTE
When operating temperatures overlap, use the lighter
grade of oil.
OIL CAPACITY
Sump. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 U.S. QUARTS
Total. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 U.S. QUARTS
(Continued Next Page)
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U.S.
1-7
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
DESCRIPTIVE DATA (Continued)
MAXIMUM CERTIFICATED WEIGHTS
Ramp Weight:
Normal Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2457 POUNDS
Utility Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2207 POUNDS
Takeoff Weight:
Normal Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2450 POUNDS
Utility Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2200 POUNDS
Landing Weight:
Normal Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2450 POUNDS
Utility Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2200 POUNDS
WEIGHT IN BAGGAGE COMPARTMENT, NORMAL CATEGORY
Baggage Area A (Station 82 to 108). . . . . . . . . . . . . . . . . 120 POUNDS
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to note below.
Baggage Area B (Station 108 to 142). . . . . . . . . . . . . . . . . 50 POUNDS
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to note below.
NOTE
The maximum allowable combined weight capacity for
baggage in areas A and B is 120 pounds.
WEIGHT IN BAGGAGE COMPARTMENT, UTILITY CATEGORY
In this category, the rear seat must not be occupied and the baggage
compartment must be empty.
(Continued Next Page)
1-8
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
DESCRIPTIVE DATA (Continued)
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight . . . . . . . . . . . . . . . . . . . . . . . . . 1639 POUNDS
Maximum Useful Load, Normal Category . . . . . . . . . . . . 818 POUNDS
Maximum Useful Load, Utility Category. . . . . . . . . . . . . . 568 POUNDS
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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1 lbs/sq. ft.
Power Loading. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.3 lbs/HP
172RPHBUS-00
U.S.
1-9
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
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.
VA
Maneuvering Speed is the maximum speed at which full or
abrupt control movements may be used without
overstressing the airframe.
VFE
Maximum Flap Extended Speed is the highest speed
permissible with wing flaps in a prescribed extended
position.
VNO
Maximum Structural Cruising Speed is the speed that
should not be exceeded except in smooth air, then only with
caution.
VNE
Never Exceed Speed is the speed limit that may not be
exceeded at any time.
VS
Stalling Speed or the minimum steady flight speed is the
minimum speed at which the airplane is controllable.
VSO
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.
Vx
Best Angle of Climb Speed is the speed which results in
the greatest gain of altitude in a given horizontal distance.
VY
Best Rate of Climb Speed is the speed which results in the
greatest gain in altitude in a given time.
(Continued Next Page)
1-10
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
(Continued)
METEOROLOGICAL TERMINOLOGY
OAT
Outside Air Temperature is the free air static
temperature. It may be expressed in either degrees
Celsius or degrees Fahrenheit.
Standard
Temperature
Standard Temperature is 15°C at sea level pressure
altitude and decreases by 2°C for each 1000 feet of
altitude.
Pressure
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
BHP
Brake Horsepower is the power developed by the
engine.
RPM
Revolutions Per Minute is engine speed.
Static RPM
Static RPM is engine speed attained during a full
throttle engine runup when the airplane is on the
ground and stationary.
Lean
Mixture
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.
(Continued Next Page)
172RPHBUS-00
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1-11
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
(Continued)
ENGINE POWER TERMINOLOGY (Continued)
Rich
Mixture
Full
Rich
Idle
Cutoff
Full
Throttle
Closed
Throttle
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).
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.
(Continued Next Page)
1-12
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
(Continued)
AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
Demonstrated
Crosswind
Velocity
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
Usable Fuel is the fuel available for flight planning.
Unusable
Fuel
Unusable Fuel is the quantity of fuel that can not be
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
Datum
Course Datum is the compass reference used by the
autopilot, along with course deviation, to provide
lateral control when tracking a navigation signal.
(Continued Next Page)
172RPHBUS-00
U.S.
1-13
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
(Continued)
WEIGHT AND BALANCE TERMINOLOGY
Reference
Datum
Reference Datum is an imaginary vertical plane from
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 POH to simplify balance
calculations by reducing the number of digits.)
Center of
Gravity
(C.G.)
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.
C.G. Arm
Center of Gravity Arm is the arm obtained by adding
the airplane's individual moments and dividing the sum
by the total weight.
C.G. Limits
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
Standard Empty Weight is the weight of a standard
airplane, including unusable fuel, full operating fluids
and full engine oil.
(Continued Next Page)
1-14
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
(Continued)
WEIGHT AND BALANCE TERMINOLOGY (Continued)
Basic Empty
Weight
Basic Empty Weight is the standard empty weight
plus the weight of optional equipment.
Useful Load
Useful Load is the difference between ramp weight
and the basic empty weight.
MAC
MAC (Mean Aerodynamic Chord) is a chord of an
imaginary rectangular airfoil having the same pitching
moments throughout the flight range as that of the
actual wing.
Maximum
Ramp
Weight
Maximum
Takeoff
Weight
Maximum
Landing
Weight
Tare
172RPHBUS-00
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.
U.S.
1-15
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
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)."
Please refer to the following pages for these charts.
1-16
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
WEIGHT CONVERSIONS
Figure 1-2 (Sheet 1 of 2)
172RPHBUS-00
U.S.
1-17
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
WEIGHT CONVERSIONS
Figure 1-2 (Sheet 2)
1-18
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
LENGTH CONVERSIONS
Figure 1-3 (Sheet 1 of 4)
172RPHBUS-00
U.S.
1-19
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
LENGTH CONVERSIONS
Figure 1-3 (Sheet 2)
1-20
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
LENGTH CONVERSIONS
Figure 1-3 (Sheet 3)
172RPHBUS-00
U.S.
1-21
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
LENGTH CONVERSIONS
Figure 1-3 (Sheet 4)
1-22
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
DISTANCE CONVERSIONS
Figure 1-4
172RPHBUS-00
U.S.
1-23
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
VOLUME CONVERSIONS
Figure 1-5 (Sheet 1 of 3)
1-24
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
VOLUME CONVERSIONS
Figure 1-5 (Sheet 2)
172RPHBUS-00
U.S.
1-25
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
VOLUME CONVERSIONS
Figure 1-5 (Sheet 3)
1-26
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
TEMPERATURE CONVERSIONS
Figure 1-6
172RPHBUS-00
U.S.
1-27
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PRESSURE CONVERSION
HECTOPASCALS TO INCHES OF MERCURY
Figure 1-7
1-28
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 1
GENERAL
VOLUME TO WEIGHT CONVERSION
Figure 1-8
172RPHBUS-00
U.S.
1-29
SECTION 1
GENERAL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
QUICK CONVERSIONS
Figure 1-9
1-30
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
OPERATING LIMITATIONS
TABLE OF CONTENTS
Page
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3
Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4
Airspeed Indicator Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5
Powerplant Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6
Powerplant Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
Weight Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8
Normal Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8
Maximum Weight in Baggage Compartment - Normal Category . 2-8
Utility Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8
Maximum Weight in Baggage Compartment - Utility Category . . . 2-8
Center Of Gravity Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9
Normal Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9
Utility Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9
Maneuver Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10
Normal Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10
Utility Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10
Flight Load Factor Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11
Normal Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11
Utility Category . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11
Kinds Of Operations Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12
Kinds Of Operations Equipment List . . . . . . . . . . . . . . . . . . . . . . 2-13
Fuel Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18
Flap Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18
System Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19
Aux Audio System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19
12V Power System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19
G1000 Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-20
Garmin GFC 700 AFCS (if installed) . . . . . . . . . . . . . . . . . . . . . . 2-21
Terrain Awareness and Warning System (TAWS-B) . . . . . . . . . . 2-22
Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23
FAA APPROVED
172RPHBUS-00
U.S.
2-1/2-2
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
INTRODUCTION
Section 2 includes operating limitations, instrument markings, and
basic placards necessary for the safe operation of the airplane, its
engine, standard systems and standard equipment. The limitations
included in this section and in Section 9 have been approved by the
Federal Aviation Administration. Observance of these operating
limitations is required by Federal Aviation Regulations.
NOTE
•
Refer to Supplements, Section 9 of this Pilot's Operating
Handbook for amended operating limitations, operating
procedures, performance data and other necessary
information for airplanes equipped with specific options.
•
The airspeeds listed in Figure 2-1, Airspeed Limitations,
and Figure 2-2, Airspeed Indicator Markings, are based
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
5.
The Cessna Model No. 172R is certificated under FAA Type Certificate
No. 3A12.
FAA APPROVED
172RPHBUS-00
U.S.
2-3
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown in
Figure 2-1. Maneuvering speeds shown apply to normal category
operations. The utility category maneuvering speed is 94 KIAS at 2200
pounds.
AIRSPEED LIMITATIONS
SYMBOL
SPEED
KCAS
KIAS
REMARKS
VNE
Never Exceed Speed
160
163
Do not exceed this speed
in any operation.
VNO
Maximum Structural
Cruising Speed
126
129
Do not exceed this speed
except in smooth air, and
then only with caution.
VA
Maneuvering Speed:
2450 Pounds
2200 Pounds
1600 Pounds
VFE
Maximum Flap
Extended Speed:
FLAPS 10°
FLAPS 10° to FULL
-----
Maximum Window
Open Speed
97
93
82
99
94
82
Do not make full or abrupt
control movements above
this speed.
Do not exceed this speed
with flaps down.
108
84
110
85
160
163
Do not exceed this speed
with windows open.
Figure 2-1
2-4
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code significance are
shown in Figure 2-2.
AIRSPEED INDICATOR MARKINGS
MARKING
KIAS VALUE OR
RANGE
Red Arc*
20 - 33
Low airspeed warning.
White Arc
33 - 85
Full Flap Operating Range. Lower limit is
maximum weight VSO in landing configuration.
Upper limit is maximum speed permissible with
flaps extended.
Green Arc
44 - 129
Normal Operating Range. Lower limit is
maximum weight VS1 at most forward C.G.
with flaps retracted. Upper limit is maximum
structural cruising speed.
Yellow Arc
129 - 163
Operations must be conducted with caution
and only in smooth air.
Red Line
163
SIGNIFICANCE
Maximum speed for all operations.
*G1000 airspeed indicator only.
Figure 2-2
FAA APPROVED
172RPHBUS-00
U.S.
2-5
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
POWERPLANT LIMITATIONS
Engine Manufacturer: Textron Lycoming
Engine Model Number: IO-360-L2A
Maximum Power: 160 BHP Rating
Engine Operating Limits for Takeoff and Continuous Operations:
Maximum Engine Speed:. . . . . . . . . . . . . . . . . . . . . . . . . .2400 RPM
NOTE
The static RPM range at full throttle is 2065 - 2165 RPM.
Maximum Oil Temperature: . . . . . . . . . . . . . . . . . . . . .245°F (118°C)
Oil Pressure, Minimum: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20 PSI
Oil Pressure, Maximum: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 115 PSI
CAUTION
ENGINE OPERATION WITH INDICATED OIL PRESSURE
BELOW THE GREEN BAND RANGE WHILE IN CRUISE
OR CLIMB CONFIGURATION IS CONSIDERED
ABNORMAL AND SHOULD BE INSPECTED BY
QUALIFIED MAINTENANCE PERSONNEL BEFORE
NEXT FLIGHT.
Fuel Grade: Refer to Fuel Limitations
Oil Grade (Specification):
MIL-L-6082 or SAE J1966 Aviation Grade Straight Mineral Oil or
MIL-L-22851 or SAE J1899 Ashless Dispersant Oil. Oil must comply
with the latest revision and/or supplement for Textron Lycoming
Service Instruction No. 1014, must be used.
Propeller Manufacturer: McCauley Propeller Systems
Propeller Model Number: 1C235/LFA7570
Propeller Diameter:
Maximum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75 INCHES
Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74 INCHES
2-6
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
POWERPLANT INSTRUMENT MARKINGS
Powerplant instrument markings and their color code significance are
shown in Figure 2-3. Operation with indications in the red range is
prohibited. Avoid operating with indicators in the yellow range.
POWERPLANT INSTRUMENT MARKINGS
INSTRUMENT
RED LINE
(MIN)
GREEN ARC
RED ARC YELLOW (NORMAL
OPERATING
(LWR)
ARC
RANGE)
RED ARC
(UPR)
Tachometer
----
----
----
1900 to 2400 2400* to 2700
RPM
RPM
Cylinder Head
Temperature
----
----
----
200 to 500°F
Oil
Temperature
----
----
----
100 to 245°F 245* to 250°F
Oil Pressure
----
0 to 20 PSI
----
50 to 90 PSI
115* to 120
PSI
Fuel Quantity
0 (1.5
Gallons
Unusable
Each
Tank)
----
0 to 5
Gallons
5 to 24
Gallons
----
Fuel Flow
----
----
----
0 to 11 GPH
----
Vacuum
Indicator
----
----
----
4.5 to 5.5
in.hg.
----
----
*Maximum operating limit is lower end of red arc.
Figure 2-3
FAA APPROVED
172RPHBUS-00
U.S.
2-7
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
WEIGHT LIMITS
NORMAL CATEGORY
Maximum Ramp Weight: . . . . . . . . . . . . . . . . . . . . . . 2457 POUNDS
Maximum Takeoff Weight: . . . . . . . . . . . . . . . . . . . . . 2450 POUNDS
Maximum Landing Weight: . . . . . . . . . . . . . . . . . . . . 2450 POUNDS
MAXIMUM WEIGHT IN BAGGAGE COMPARTMENT - NORMAL
CATEGORY:
Baggage Area A - Station 82 to 108: . . . . . . . . . . . . . 120 POUNDS
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to note below.
Baggage Area B - Station 108 to 142: . . . . . . . . . . . . . 50 POUNDS
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refer to note below.
NOTE
The maximum allowable combined weight capacity for
baggage in areas A and B is 120 pounds.
UTILITY CATEGORY
Maximum Ramp Weight: . . . . . . . . . . . . . . . . . . . . . . 2207 POUNDS
Maximum Takeoff Weight: . . . . . . . . . . . . . . . . . . . . . 2200 POUNDS
Maximum Landing Weight: . . . . . . . . . . . . . . . . . . . . 2200 POUNDS
MAXIMUM WEIGHT IN BAGGAGE COMPARTMENT - UTILITY
CATEGORY:
The baggage compartment must be empty and rear seat must not
be occupied.
2-8
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
CENTER OF GRAVITY LIMITS
NORMAL CATEGORY
Center Of Gravity Range:
Forward: 35.0 inches aft of datum at 1950 pounds or less, with
straight line variation to 40.0 inches aft of datum at 2450
pounds.
Aft:
47.3 inches aft of datum at all weights.
Reference Datum: Lower portion of front face of firewall.
UTILITY CATEGORY
Center of Gravity Range:
Forward: 35.0 inches aft of datum at 1950 pounds or less, with
straight line variation to 37.5 inches aft of datum at 2200
pounds.
Aft:
40.5 inches aft of datum at all weights.
Reference Datum: Lower portion of front face of firewall.
FAA APPROVED
172RPHBUS-00
U.S.
2-9
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
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. These include any maneuvers incidental to normal flying,
stalls (except whip stalls), lazy eights, chandelles, and turns in which
the angle of bank is not more than 60°.
NORMAL CATEGORY MANEUVERS AND RECOMMENDED ENTRY
SPEED*
Chandelles. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 KNOTS
Lazy Eights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 KNOTS
Steep Turns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 KNOTS
Stalls (Except Whip Stalls) . . . . . . . . . . . . . . . . . . .Slow Deceleration
* Abrupt use of the controls is prohibited above 99 KNOTS.
UTILITY CATEGORY
This airplane is not designed for purely aerobatic flight. However, in the
acquisition of various certificates such as commercial pilot and flight
instructor, certain maneuvers are required by the FAA. All of these
maneuvers are permitted in this airplane when operated in the utility
category.
In the utility category, the rear seat must not be occupied and the
baggage compartment must be empty.
UTILITY CATEGORY MANEUVERS AND RECOMMENDED ENTRY
SPEED*
Chandelles. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 KNOTS
Lazy Eights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 KNOTS
Steep Turns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 KNOTS
Spins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Slow Deceleration
Stalls (Except Whip Stalls) . . . . . . . . . . . . . . . . . . .Slow Deceleration
* Abrupt use of the controls is prohibited above 94 KNOTS.
(Continued Next Page)
2-10
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
MANEUVER LIMITS (Continued)
UTILITY CATEGORY (Continued)
Aerobatics that may impose high loads should not be attempted. The
important thing to bear in mind in flight maneuvers is that the airplane is
clean in aerodynamic design and will build up speed quickly with the
nose down. Proper speed control is an essential requirement for
execution of any maneuver, and care should always be exercised to
avoid excessive speed which in turn can impose excessive loads. In
the execution of all maneuvers, avoid abrupt use of controls.
FLIGHT LOAD FACTOR LIMITS
NORMAL CATEGORY
Flight Load Factors (Maximum Takeoff Weight - 2450 POUNDS):
*Flaps UP: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .+3.8g, -1.52g
*Flaps FULL: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +3.0g
* The design load factors are 150% of the above, and in all cases,
the structure meets or exceeds design loads.
UTILITY CATEGORY
Flight Load Factors (Maximum Takeoff Weight - 2200 POUNDS):
*Flaps UP: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .+4.4g, -1.76g
*Flaps FULL: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +3.0g
* The design load factors are 150% of the above, and in all cases,
the structure meets or exceeds design loads.
FAA APPROVED
172RPHBUS-00
U.S.
2-11
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
KINDS OF OPERATIONS LIMITS
The Cessna 172R Nav III airplane is approved for day and night, VFR
and IFR operations. Flight into known icing conditions is prohibited.
The minimum equipment for approved operations required under the
Operating Rules are defined by 14 CFR 91 and 14 CFR 135, as
applicable.
The following Kinds of Operations Equipment List (KOEL) identifies the
equipment required to be operational for airplane airworthiness in the
listed kind of operations.
2-12
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
KINDS OF OPERATIONS EQUIPMENT LIST
System, Instrument, Equipment
and/or Function
PLACARDS AND MARKINGS
1 - 172R Nav III - GFC 700
AFCS POH/AFM
2 - Garmin G1000 Cockpit
Reference Guide
AIR CONDITIONING
1 - Forward Avionics Fan
2 - PFD Fan
3 - MFD Fan
4 - Aft Avionics Fan
COMMUNICATIONS
1 - VHF COM
ELECTRICAL POWER
1 - 24V Main Battery
2 - 28V Alternator
3 - 24V Standby Battery
4 - Main Ammeter
5 - Standby Ammeter
KIND OF OPERATION
V
I
V
I
F
F
F
F
R
R
R
R
N
N
D
D
I
I
A
A
G
G
Y
Y
H
H
T
T
COMMENTS
1
1
1
1
Accessible to pilot
in flight.
1
1
1
1
Accessible to pilot
in flight.
1
0
0
1
1
0
0
1
1
0
0
1
1
0
0
1
0
0
1
1
1
1
0
1
0
1
1
*
1
*
1
1
*
1
*
1
1
*
1
*
* Refer to Note 1.
* Refer to Note 1.
NOTE
1. The European Aviation Safety Agency (EASA) requires the
24V Standby Battery and Standby Ammeter to successfully
complete the pre-flight check before operating the airplane in
VFR night, IFR day, or IFR night conditions in Europe. Correct
operation of the 24V Standby Battery and Standby Ammeter is
recommended for all other operations.
(Continued Next Page)
FAA APPROVED
172RPHBUS-00
U.S.
2-13
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
KINDS OF OPERATIONS EQUIPMENT LIST (Continued)
System, Instrument, Equipment
and/or Function
EQUIPMENT AND FURNISHINGS
1 - Seat Belt Assembly
2 - Shoulder Harness
FLIGHT CONTROLS
1 - Flap Position Indicator
2 - Flap Motor
3 - Elevator Trim System
4 - Elevator Trim Indicator
FUEL SYSTEM
1 - Electric Fuel Pump
2 - Fuel Quantity Indicator - L Tank
3 - Fuel Quantity Indicator - R Tank
ICE AND RAIN PROTECTION
1 - Alternate Static Air Source
2 - Alternate Induction Air System
INDICATING/RECORDING
SYSTEM
1 - Stall Warning System
2 - System Annunciator and
Warning Displays
LANDING GEAR
1 - Wheel Fairings
KIND OF OPERATION
V
I
F
F
V
I
R
R
F
F
R
R
N
N
I
D
D
I
G
A
A
G
H
Y
Y
H
T
T
COMMENTS
1
1
1
1
Each Seat
Occupant
1
1
1
1
Front Seat
Occupants
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
0
0
0
0
1
1
1
1
1
1
1
1
1
1
1
1
0
0
0
0
Removable
(Continued Next Page)
2-14
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
KINDS OF OPERATIONS EQUIPMENT LIST (Continued)
System, Instrument, Equipment
and/or Function
LIGHTING
1 - PFD Bezel Lighting
KIND OF OPERATION
V
I
V
F
I
F
F
F
R
R
R
R
N
N
D
D
I
I
A
G
A
G
Y
H
Y
H
T
T
0
0
0
1
2 - PFD Backlighting
3 - MFD Bezel Lighting
4 - MFD Backlighting
5 - Switch and Circuit Breaker
Panel Lighting
*
0
*
0
1
0
1
1
1
0
1
0
1
1
1
1
6 - Standby Airspeed Indicator
Internal Lighting
7 - Standby Altimeter Internal
Lighting
0
1
0
1
0
1
0
1
8 - Non-stabilized Magnetic
Compass Internal Lighting
0
1
0
1
9 - Standby Attitude Indicator
Internal Lighting
10 - Cockpit Flood Light
11 - Aircraft Position (NAV) Lights
12 - STROBE Light System
13 - BEACON Light
14 - TAXI Light
15 - LAND (Landing) Light
0
1
0
1
0
0
1
0
0
0
1
1
1
0
0
1
0
1
1
0
0
0
1
1
1
0
0
1
COMMENTS
*Refer to Note 2.
*Refer to Note 3.
Operations for hire
only.
NOTE
2. PFD backlighting is required for day VFR flight if MFD
backlighting has failed. Display backup mode must be active
so engine indicators are shown.
3. MFD backlighting is required for day VFR flight if PFD
backlighting has failed. Display backup mode must be active
so flight instruments are shown.
(Continued Next Page)
FAA APPROVED
172RPHBUS-00
U.S.
2-15
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
KINDS OF OPERATIONS EQUIPMENT LIST (Continued)
System, Instrument, Equipment
and/or Function
NAVIGATION AND PITOTSTATIC SYSTEM
KIND OF OPERATION
V
I
V
F
I
F
F
F
R
R
R
R
N
N
D
D
I
I
A
G
A
G
Y
H
Y
H
T
T
COMMENTS
1 - G1000 Airspeed Indicator
2 - Standby Airspeed Indicator
3 - G1000 Altimeter
4 - Standby Altimeter
5 - G1000 Vertical Speed
Indicator
1
0
1
0
0
1
0
1
0
0
1
1
1
1
0
1
1
1
1
0
6 - G1000 Attitude Indicator
7 - Standby Attitude Indicator
8 - G1000 Directional Indicator
(HSI)
9 - G1000 Turn Coordinator
10 - Non-stabilized Magnetic
Compass
11 - VHF Navigation Radio
(VOR/LOC/GS)
12 - GPS Receiver/Navigator
0
0
0
0
0
0
1
1
1
1
1
1
0
1
0
1
1
1
1
1
0
0
A/R
A/R As Required Per
Procedure.
0
0
A/R
13 - Marker Beacon Receiver
0
0
A/R
A/R
A/R
1
A/R As Required Per
Procedure.
A/R As Required Per
Procedure.
1 As Required Per
Procedure.
15 - Clock
0
0
1
1
16 - GFC 700 AFCS (if installed)
0
0
0
0
14 - Blind Altitude Encoder
(Continued Next Page)
2-16
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
KINDS OF OPERATIONS EQUIPMENT LIST (Continued)
System, Instrument, Equipment
and/or Function
VACUUM
1 - Engine Driven Vacuum
Pump
2 - Vacuum Indicator
ENGINE FUEL AND CONTROL
1 - Fuel Flow Indicator
ENGINE INDICATING
1 - Tachometer (RPM)
2 - Cylinder Head Temperature
(CHT) Indicator
3 - Oil Pressure Indicator
4 - Oil Temperature Indicator
ENGINE OIL
1 - Engine Crankcase Dipstick
FAA APPROVED
172RPHBUS-00
KIND OF OPERATION
V
I
V
F
I
F
F
F
R
R
R
R
N
N
D
D
I
I
A
G
A
G
Y
H
Y
H
T
T
0
0
1
1
0
0
1
1
1
1
1
1
1
0
1
0
1
0
1
0
1
1
1
1
1
1
1
1
1
1
1
1
U.S.
COMMENTS
2-17
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FUEL LIMITATIONS
Total Fuel: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .56.0 U.S. GALLONS
(28.0 GALLONS per tank)
Usable Fuel (all flight conditions): . . . . . . . . . . . . .53.0 U.S. GALLONS
(26.5 GALLONS per tank)
Unusable Fuel: . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3.0 U.S. GALLONS
(1.5 GALLONS per tank)
NOTE
To e n s u r e m a x i m u m f u e l c a p a c i t y a n d m i n i m i z e
crossfeeding 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 definition.
Takeoff and land with the fuel selector valve handle in the BOTH
position.
Maximum slip or skid duration with one tank dry: 30 seconds
Operation on either LEFT or RIGHT tank limited to level flight only.
With 1/4 tank or less, prolonged uncoordinated flight is prohibited when
operating on either left or right tank.
Fuel remaining in the tank after the fuel quantity indicator reads 0 (red
line) cannot be safely used in flight.
Approved Fuel Grades (And Colors):
100LL Grade Aviation Fuel (Blue)
100
Grade Aviation Fuel (Green)
FLAP LIMITATIONS
Approved Takeoff Range: . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP to 10°
Approved Landing Range: . . . . . . . . . . . . . . . . . . . . . . . . . .UP to FULL
2-18
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
SYSTEM LIMITATIONS
AUX AUDIO SYSTEM
Use of the AUX AUDIO IN entertainment input is prohibited during
takeoff and landing.
Use of the AUX AUDIO IN entertainment audio input and portable
electronic devices (PED), such as cellular telephones, games,
cassette, CD or MP3 players, is prohibited under IFR unless the
operator of the airplane has determined that the use of the Aux Audio
System and the connected portable electronic device(s) will not cause
interference with the navigation or communication system of the
airplane.
12V POWER SYSTEM
The 12 Volt Power System (POWER OUTLET 12V - 10A) is not
certified for supplying power to flight-critical communications or
navigation devices.
Use of the 12 Volt Power System is prohibited during takeoff and
landing.
Use of the 12 Volt Power System is prohibited under IFR unless the
operator of the airplane has determined that the use of the 12 VDC
power supply and connected portable electronic device(s) will not
cause interference with the navigation or communication systems of
the airplane.
FAA APPROVED
172RPHBUS-00
U.S.
2-19
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
G1000 LIMITATIONS
The current Garmin G1000 Cockpit Reference Guide (CRG) Part
Number and System Software Version that must be available to the
pilot during flight are displayed on the MFD AUX group, SYSTEM
STATUS page.
GPS based IFR enroute, oceanic and terminal navigation is prohibited
unless the pilot verifies the currency of the database or verifies each
selected waypoint for accuracy by reference to current approved data.
RNAV/GPS instrument approaches must be accomplished in
accordance with approved instrument approach procedures that are
retrieved from the G1000 navigation database. The G1000 database
must incorporate the current update cycle.
Use of the NAVIGATION MAP page for pilotage navigation is
prohibited. The Navigation Map is intended only to enhance situational
awareness. Navigation is to be conducted using only current charts,
data and authorized navigation facilities.
Use of the TRAFFIC MAP to maneuver the airplane to avoid traffic is
prohibited. The Traffic Information System (TIS) is intended for advisory
use only. TIS is intended only to help the pilot to visually locate traffic. It
is the responsibility of the pilot to see and maneuver to avoid traffic.
Use of the TERRAIN PROXIMITY information for primary terrain
avoidance is prohibited. The Terrain Proximity map is intended only to
enhance situational awareness. It is the pilot’s responsibility to provide
terrain clearance at all times.
Navigation using the G1000 is not authorized north of 70° North latitude
or south of 70° South latitude due to unsuitability of the magnetic fields
near the Earth's poles. In addition, operations are not authorized in the
following two regions:
1. North of 65° North latitude between longitude 75° W and 120° W
(Northern Canada).
2. South of 55° South latitude between longitude 120° E and 165° E
(region south of Australia and New Zealand).
(Continued Next Page)
2-20
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
G1000 LIMITATIONS (Continued)
The COM 1/2 (split COM) function of the Audio Panel is not approved
for use. During COM 1/2 operation, transmission by one crew member
inhibits reception by the other crew member.
The fuel quantity, fuel used and fuel remaining functions of the G1000
are supplemental information only and must be verified by the pilot.
GARMIN GFC 700 AFCS (if installed)
1. The GFC 700 AFCS preflight test must be successfully
completed prior to use of the autopilot, flight director or manual
electric trim.
2. A pilot, with the seat belt fastened, must occupy the left pilot’s
seat during all autopilot operations.
3. The autopilot must be off during all takeoff and landings.
4. Autopilot maximum engagement speed - 150 KIAS.
Autopilot minimum engagement speed - 70 KIAS.
Electric Trim maximum operating speed - 163 KIAS.
5. Maximum fuel imbalance with autopilot engaged - 90 pounds.
6. The autopilot must be disengaged below 200 feet AGL during
approach operations and below 800 feet AGL during all other
operations.
7. ILS approaches using the autopilot/flight director are limited to
Category I approaches only.
8. Use of the autopilot is prohibited when the audio panel is
inoperative, since the aural alert will not be provided when
autopilot is disengaged.
9. Use of the autopilot is prohibited when conducting missed
approach procedures until an established rate of climb that
ensures all altitude requirements of the procedure will be met.
(Continued Next Page)
FAA APPROVED
172RPHBUS-00
U.S.
2-21
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
G1000 LIMITATIONS (Continued)
TERRAIN AWARENESS AND WARNING SYSTEM
(TAWS-B)
Use of the Terrain Awareness and Warning System (TAWS-B) to
navigate to avoid terrain or obstacles is prohibited. TAWS-B is only
approved as an aid to help the pilot to see-and-avoid terrain or
obstacles.
TAWS-B must be inhibited when landing at a location not included in
the airport database.
Use of TAWS-B is prohibited when operating using the QFE altimeter
setting (altimeter indicates 0 feet altitude when the airplane is on the
runway).
The pilot is authorized to deviate from the current ATC clearance only
to the extent necessary to comply with TAWS-B warnings.
The geographic area of the TAWS-B database must match the
geographic area in which the airplane is being operated.
2-22
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
PLACARDS
The following information must be displayed in the form of composite or
individual placards.
1. In full view of the pilot: (The "DAY-NIGHT-VFR-IFR" entry,
shown on the example below, will vary with installed equipment).
2. On control lock:
(Continued Next Page)
FAA APPROVED
172RPHBUS-00
U.S.
2-23
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PLACARDS (Continued)
3. On the fuel selector valve:
4. Near both fuel tank filler cap:
(Continued Next Page)
2-24
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
PLACARDS (Continued)
5. On flap control indicator:
6. In baggage compartment:
(Continued Next Page)
FAA APPROVED
172RPHBUS-00
U.S.
2-25
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PLACARDS (Continued)
7. A calibration card must be provided to indicate the accuracy of
the magnetic compass in 30° increments.
8. Molded on the oil filler cap/dipstick:
9. Silk-screened on the instrument panel directly above the PFD:
(Continued Next Page)
2-26
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 2
OPERATING LIMITATIONS
PLACARDS (Continued)
10. Silk-screened on the upper right instrument panel:
11. On auxiliary power plug door and second placard on battery
box:
12. On the upper right side of the aft cabin partition:
or
(Continued Next Page)
FAA APPROVED
172RPHBUS-00
U.S.
2-27
SECTION 2
OPERATING LIMITATIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PLACARDS (Continued)
13. On the center overhead flood light control switch:
2-28
U.S.
FAA APPROVED
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
EMERGENCY PROCEDURES
TABLE OF CONTENTS
Page
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5
Airspeeds For Emergency Operations. . . . . . . . . . . . . . . . . . . . . . . . 3-5
EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . 3-6
ENGINE FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6
Engine Failure During Takeoff Roll . . . . . . . . . . . . . . . . . . . . . . . . 3-6
Engine Failure Immediately After Takeoff . . . . . . . . . . . . . . . . . . . 3-6
Engine Failure During Flight (Restart Procedures) . . . . . . . . . . . . 3-7
FORCED LANDINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-8
Emergency Landing Without Engine Power . . . . . . . . . . . . . . . . . 3-8
Precautionary Landing With Engine Power. . . . . . . . . . . . . . . . . . 3-8
Ditching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-9
FIRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-10
During Start On Ground . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-10
Engine Fire In Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11
Electrical Fire In Flight. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11
Cabin Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-12
Wing Fire. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13
ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-14
Inadvertent Icing Encounter During Flight . . . . . . . . . . . . . . . . . . 3-14
STATIC SOURCE BLOCKAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15
(Erroneous Instrument Reading Suspected). . . . . . . . . . . . . . . .3-15
EXCESSIVE FUEL VAPOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15
Fuel Flow Stabilization Procedures . . . . . . . . . . . . . . . . . . . . . . .3-15
(Continued Next Page)
172RPHBUS-00
U.S.
3-1
SECTION 3
EMERGENCY PROCEDURES
TABLE OF CONTENTS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
(Continued)
Page
ABNORMAL LANDINGS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16
Landing With A Flat Main Tire . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16
Landing With A Flat Nose Tire . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16
ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS . . .
High Volts Annunciator Comes On or
M BATT AMPS More Than 40 . . . . . . . . . . . . . . . . . . . . . . . .
LOW VOLTS Annunciator Comes On Below 1000 RPM . . . . . .
LOW VOLTS Annunciator Comes On or
Does Not Go Off at Higher RPM. . . . . . . . . . . . . . . . . . . . . . .
3-17
3-17
3-19
3-19
AIR DATA SYSTEM FAILURE. . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-21
Red X - PFD Airspeed Indicator . . . . . . . . . . . . . . . . . . . . . . . . 3-21
Red X - PFD Altitude Indicator . . . . . . . . . . . . . . . . . . . . . . . . . 3-21
ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS)
FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-21
Red X - PFD Attitude Indicator . . . . . . . . . . . . . . . . . . . . . . . . . 3-21
Red X - Horizontal Situation Indicator (HSI) . . . . . . . . . . . . . . . 3-21
AUTOPILOT OR ELECTRIC TRIM FAILURE (if installed) . . . . . . 3-22
AP or PTRM Annunciator(s) Come On . . . . . . . . . . . . . . . . . . . 3-22
DISPLAY COOLING ADVISORY. . . . . . . . . . . . . . . . . . . . . . . . . . 3-23
PFD1 COOLING or MFD1 COOLING Annunciator(s) Come On 3-23
VACUUM SYSTEM FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-23
LOW VACUUM Annunciator Comes On . . . . . . . . . . . . . . . . . . 3-23
HIGH CARBON MONOXIDE (CO) LEVEL ADVISORY . . . . . . . . 3-24
CO LVL HIGH Annunciator Comes On . . . . . . . . . . . . . . . . . . . 3-24
CO LVL HIGH Annunciator Remains On . . . . . . . . . . . . . . . . . . 3-24
(Continued Next Page)
3-2
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
TABLE OF CONTENTS
SECTION 3
EMERGENCY PROCEDURES
(Continued)
Page
AMPLIFIED EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . 3-25
Engine Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-25
Maximum Glide . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-26
Forced Landings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-27
Landing Without Elevator Control . . . . . . . . . . . . . . . . . . . . . . . . . . 3-28
Fires . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-28
Emergency Operation In Clouds . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-29
Executing A 180° Turn In Clouds (AHRS FAILED) . . . . . . . . . . .3-29
Emergency Descent Through Clouds (AHRS FAILED) . . . . . . . 3-30
Recovery From Spiral Dive In The Clouds (AHRS FAILED) . . . .3-31
Inadvertent Flight Into Icing Conditions . . . . . . . . . . . . . . . . . . . . . . 3-31
Static Source Blocked . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-32
Spins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-32
Rough Engine Operation Or Loss Of Power . . . . . . . . . . . . . . . . . . 3-33
Spark Plug Fouling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-33
Magneto Malfunction. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-33
Idle Power Engine Roughness . . . . . . . . . . . . . . . . . . . . . . . . . . 3-33
Engine-Driven Fuel Pump Failure . . . . . . . . . . . . . . . . . . . . . . . . 3-34
Excessive Fuel Vapor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-34
Low Oil Pressure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-35
Electrical Power Supply System Malfunctions . . . . . . . . . . . . . . . . . 3-36
Excessive Rate Of Charge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-36
Insufficient Rate Of Charge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-37
High Carbon Monoxide (CO) Level Annunciation . . . . . . . . . .3-39/3-40
Other Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-39/3-40
Windshield Damage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-39/3-40
172RPHBUS-00
U.S.
3-3/3-4
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
INTRODUCTION
Section 3 provides checklist and amplified procedures for coping with
emergencies that may occur. Emergencies caused by airplane or
engine malfunctions are extremely rare if proper preflight inspections
and maintenance are practiced. Enroute weather emergencies can be
minimized or eliminated by careful flight planning and good judgment
when unexpected weather is encountered. However, should an
emergency arise, the basic guidelines described in this section should
be considered and applied as necessary to correct the problem. In any
emergency situation, the most important task is continued control of the
airplane and maneuver to execute a successful landing.
Emergency procedures associated with optional or supplemental
equipment are found in Section 9, Supplements.
AIRSPEEDS FOR EMERGENCY OPERATIONS
ENGINE FAILURE AFTER TAKEOFF
Wing Flaps UP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65 KIAS
Wing Flaps 10° - FULL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60 KIAS
MANEUVERING SPEED
2450 POUNDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99 KIAS
2200 POUNDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94 KIAS
1600 POUNDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 KIAS
MAXIMUM GLIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65 KIAS
PRECAUTIONARY LANDING WITH ENGINE POWER. . . . . . 60 KIAS
LANDING WITHOUT ENGINE POWER
Wing Flaps UP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65 KIAS
Wing Flaps 10° - FULL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60 KIAS
172RPHBUS-00
U.S.
3-5
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
EMERGENCY PROCEDURES
Procedures in the Emergency Procedures Checklist portion of this
section shown in bold faced type are immediate action items which
should be committed to memory.
ENGINE FAILURES
ENGINE FAILURE DURING TAKEOFF ROLL
1.
2.
3.
4.
5.
6.
7.
Throttle Control - IDLE (pull full out)
Brakes - APPLY
Wing Flaps - RETRACT
Mixture Control - IDLE CUTOFF (pull full out)
MAGNETOS Switch - OFF
STBY BATT Switch - OFF
MASTER Switch (ALT and BAT) - OFF
ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF
1. Airspeed - 65 KIAS - Flaps UP
60 KIAS - Flaps 10° - FULL
2. Mixture Control - IDLE CUTOFF (pull full out)
3. FUEL SHUTOFF Valve - OFF (pull full out)
4. MAGNETOS Switch - OFF
5. Wing Flaps - AS REQUIRED (FULL recommended)
6. STBY BATT Switch - OFF
7. MASTER Switch (ALT and BAT) - OFF
8. Cabin Door - UNLATCH
9. Land - STRAIGHT AHEAD
(Continued Next Page)
3-6
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
ENGINE FAILURES (Continued)
ENGINE FAILURE DURING FLIGHT (Restart Procedures)
1.
2.
3.
4.
5.
6.
Airspeed - 65 KIAS (best glide speed)
FUEL SHUTOFF Valve - ON (push full in)
FUEL SELECTOR Valve - BOTH
FUEL PUMP Switch - ON
Mixture Control - RICH (if restart has not occurred)
MAGNETOS Switch - BOTH (or START if propeller is stopped)
NOTE
I f t he pr ope ll e r i s w i n dmi l l i ng, e ngi ne w i l l res t art
automatically within a few seconds. If propeller has stopped
(possible at low speeds), turn MAGNETOS switch to
START, advance throttle slowly from idle and lean the
mixture from full rich as required to obtain smooth
operation.
7. FUEL PUMP Switch - OFF
NOTE
If the indicated fuel flow (FFLOW GPH) immediately drops
to zero, a sign of failure of the engine-driven fuel pump,
return the FUEL PUMP switch to the ON position.
172RPHBUS-00
U.S.
3-7
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FORCED LANDINGS
EMERGENCY LANDING WITHOUT ENGINE POWER
1. Pilot and Passenger Seat Backs - MOST UPRIGHT POSITION
2. Seats and Seat Belts - SECURE
3. Airspeed - 65 KIAS - Flaps UP
60 KIAS - Flaps 10° - FULL
4. Mixture Control - IDLE CUTOFF (pull full out)
5. FUEL SHUTOFF Valve - OFF (pull full out)
6. MAGNETOS Switch - OFF
7. Wing Flaps - AS REQUIRED (FULL recommended)
8. STBY BATT Switch - OFF
9. MASTER Switch (ALT and BAT) - OFF (when landing is
assured)
10. Doors - UNLATCH PRIOR TO TOUCHDOWN
11. Touchdown - SLIGHTLY TAIL LOW
12. Brakes - APPLY HEAVILY
PRECAUTIONARY LANDING WITH ENGINE POWER
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
Pilot and Passenger Seat Backs - MOST UPRIGHT POSITION
Seats and Seat Belts - SECURE
Airspeed - 60 KIAS
Wing Flaps - 20°
Selected Field - FLY OVER (noting terrain and obstructions)
Wing Flaps - FULL (on final approach)
Airspeed - 60 KIAS
STBY BATT Switch - OFF
MASTER Switch (ALT and BAT) - OFF (when landing assured)
Doors - UNLATCH PRIOR TO TOUCHDOWN
Touchdown - SLIGHTLY TAIL LOW
Mixture Control - IDLE CUTOFF (pull full out)
MAGNETOS Switch - OFF
Brakes - APPLY HEAVILY
(Continued Next Page)
3-8
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
FORCED LANDINGS (Continued)
DITCHING
1. Radio - TRANSMIT MAYDAY on 121.5 MHz, (give location,
intentions and SQUAWK 7700)
2. Heavy Objects (in baggage area) - SECURE OR JETTISON (if
possible)
3. Pilot and Passenger Seat Backs - MOST UPRIGHT POSITION
4. Seats and Seat Belts - SECURE
5. Wing Flaps - 20° - FULL
6. Power - ESTABLISH 300 FT/MIN DESCENT AT 55 KIAS
NOTE
If no power is available, approach at 65 KIAS with Flaps UP
or at 60 KIAS with Flaps 10°.
7. Approach - High Winds, Heavy Seas - INTO THE WIND
Light Winds, Heavy Swells - PARALLEL TO
SWELLS
8. Cabin Doors - UNLATCH
9. Touchdown - LEVEL ATTITUDE AT ESTABLISHED RATE OF
DESCENT
10. Face - CUSHION AT TOUCHDOWN (with folded coat)
11. ELT - ACTIVATE
12. Airplane - EVACUATE THROUGH CABIN DOORS
NOTE
If necessary, open window and flood cabin to equalize
pressure so doors can be opened.
13. Life Vests and Raft - INFLATE WHEN CLEAR OF AIRPLANE
172RPHBUS-00
U.S.
3-9
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FIRES
DURING START ON GROUND
1. MAGNETOS Switch - START (continue cranking to start the
engine)
IF ENGINE STARTS
2. Power - 1800 RPM (for a few minutes)
3. Engine - SHUTDOWN (inspect for damage)
IF ENGINE FAILS TO START
2. Throttle Control - FULL (push full in)
3. Mixture Control - IDLE CUTOFF (pull full out)
4. MAGNETOS Switch - START (continue cranking)
5. FUEL SHUTOFF Valve - OFF (pull full out)
6. FUEL PUMP Switch - OFF
7. MAGNETOS Switch - OFF
8. STBY BATT Switch - OFF
9. MASTER Switch (ALT and BAT) - OFF
10. Engine - SECURE
11. Parking Brake - RELEASE
12. Fire Extinguisher - OBTAIN (have ground attendants obtain if not
installed)
13. Airplane - EVACUATE
14. Fire - EXTINGUISH (using fire extinguisher, wool blanket, or dirt)
15. Fire Damage - INSPECT (repair or replace damaged
components and/or wiring before conducting another flight)
(Continued Next Page)
3-10
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
FIRES (Continued)
ENGINE FIRE IN FLIGHT
1.
2.
3.
4.
5.
6.
Mixture Control - IDLE CUTOFF (pull full out)
FUEL SHUTOFF Valve - OFF (pull full out)
FUEL PUMP Switch - OFF
MASTER Switch (ALT and BAT) - OFF
Cabin Vents - OPEN (as needed)
CABIN HT and CABIN AIR Control Knobs - OFF (push full in)
(to avoid drafts)
7. Airspeed - 100 KIAS (If fire is not extinguished, increase glide
speed to find an airspeed, within airspeed limitations, which will
provide an incombustible mixture)
8. Forced Landing - EXECUTE (refer to EMERGENCY LANDING
WITHOUT ENGINE POWER)
ELECTRICAL FIRE IN FLIGHT
1.
2.
3.
4.
STBY BATT Switch - OFF
MASTER Switch (ALT and BAT) - OFF
Cabin Vents - CLOSED (to avoid drafts)
CABIN HT and CABIN AIR Control Knobs - OFF (push full
in) (to avoid drafts)
5. Fire Extinguisher - ACTIVATE (if available)
6. AVIONICS Switch (BUS 1 and BUS 2) - OFF
7. All Other Switches (except MAGNETOS switch) - OFF
WARNING
AFTER THE FIRE EXTINGUISHER HAS BEEN USED,
MAKE SURE THAT THE FIRE IS EXTINGUISHED
BEFORE EXTERIOR AIR IS USED TO REMOVE SMOKE
FROM THE CABIN.
8. Cabin Vents - OPEN (when sure that fire is completely
extinguished)
9. CABIN HT and CABIN AIR Control Knobs - ON (pull full out)
(when sure that fire is completely extinguished)
(Continued Next Page)
172RPHBUS-00
U.S.
3-11
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FIRES (Continued)
ELECTRICAL FIRE IN FLIGHT (Continued)
IF FIRE HAS BEEN EXTINGUISHED AND ELECTRICAL POWER
IS NECESSARY FOR CONTINUED FLIGHT TO NEAREST
SUITABLE AIRPORT OR LANDING AREA
10. Circuit Breakers - CHECK (for OPEN circuit(s), do not reset)
11. MASTER Switch (ALT and BAT) - ON
12. STBY BATT Switch - ARM
13. AVIONICS Switch (BUS 1) - ON
14. AVIONICS Switch (BUS 2) - ON
CABIN FIRE
1.
2.
3.
4.
STBY BATT Switch - OFF
MASTER Switch (ALT and BAT) - OFF
Cabin Vents - CLOSED (to avoid drafts)
CABIN HT and CABIN AIR Control Knobs - OFF (push full
in) (to avoid drafts)
5. Fire Extinguisher - ACTIVATE (if available)
WARNING
AFTER THE FIRE EXTINGUISHER HAS BEEN USED,
MAKE SURE THAT THE FIRE IS EXTINGUISHED
BEFORE EXTERIOR AIR IS USED TO REMOVE SMOKE
FROM THE CABIN.
6. Cabin Vents - OPEN (when sure that fire is completely
extinguished)
7. CABIN HT and CABIN AIR Control Knobs - ON (pull full out)
(when sure that fire is completely extinguished)
8. Land the airplane as soon as possible to inspect for damage.
(Continued Next Page)
3-12
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
FIRES (Continued)
WING FIRE
1.
2.
3.
4.
LAND and TAXI Light Switches - OFF
NAV Light Switch - OFF
STROBE Light Switch - OFF
PITOT HEAT Switch - OFF
NOTE
Perform a sideslip to keep the flames away from the fuel
tank and cabin. Land as soon as possible using flaps only
as required for final approach and touchdown.
172RPHBUS-00
U.S.
3-13
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ICING
INADVERTENT ICING ENCOUNTER DURING FLIGHT
1. PITOT HEAT Switch - ON
2. Turn back or change altitude (to obtain an outside air
temperature that is less conducive to icing)
3. CABIN HT Control Knob - ON (pull full out)
4. Defroster Control Outlets - OPEN (to obtain maximum
windshield defroster airflow)
5. CABIN AIR Control Knob - ADJUST (to obtain maximum
defroster heat and airflow)
6. Watch for signs of induction air filter icing. A loss of engine RPM
could be caused by ice blocking the air intake filter. Adjust the
throttle as necessary to hold engine RPM. Adjust mixture as
necessary for any change in power settings.
7. Plan a landing at the nearest airport. With an extremely rapid ice
build-up, select a suitable off airport landing site.
8. With an ice accumulation of 0.25 inch or more on the wing
leading edges, be prepared for significantly higher power
requirements, higher approach and stall speeds, and a longer
landing roll.
9. Leave wing flaps retracted. With a severe ice build-up on the
horizontal tail, the change in wing wake airflow direction caused
by wing flap extension could result in a loss of elevator
effectiveness.
10. Open left window and, if practical, scrape ice from a portion of
the windshield for visibility in the landing approach.
11. Perform a landing approach using a forward slip, if necessary,
for improved visibility.
12. Approach at 65 to 75 KIAS depending upon the amount of ice
accumulation.
13. Perform landing in level attitude.
14. Missed approaches should be avoided whenever possible
because of severely reduced climb capability.
3-14
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
STATIC SOURCE BLOCKAGE
(ERRONEOUS INSTRUMENT READING SUSPECTED)
1.
2.
3.
4.
ALT STATIC AIR Valve - ON (pull full out)
Cabin Vents - CLOSED
CABIN HT and CABIN AIR Control Knobs - ON (pull full out)
Airspeed - Refer to Section 5, Figure 5-1 (Sheet 2) Airspeed
Calibration, Alternate Static Source correction chart.
EXCESSIVE FUEL VAPOR
FUEL FLOW STABILIZATION PROCEDURES
(If flow fluctuations of 1 GPH or more, or power surges
occur.)
1. FUEL PUMP Switch - ON
2. Mixture Control - ADJUST (as necessary for smooth engine
operation)
3. Fuel Selector Valve - SELECT OPPOSITE TANK (if vapor
symptoms continue)
4. FUEL PUMP Switch - OFF (after fuel flow has stabilized)
172RPHBUS-00
U.S.
3-15
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ABNORMAL LANDINGS
LANDING WITH A FLAT MAIN TIRE
1. Approach - NORMAL
2. Wing Flaps - FULL
3. Touchdown - GOOD MAIN TIRE FIRST (hold airplane off flat tire
as long as possible with aileron control)
4. Directional Control - MAINTAIN (using brake on good wheel as
required)
LANDING WITH A FLAT NOSE TIRE
1. Approach - NORMAL
2. Wing Flaps - AS REQUIRED
85 to 110 KIAS - Flaps UP - 10°
Below 85 KIAS - Flaps 10° - FULL
3. Touchdown - ON MAINS (hold nosewheel off the ground as long
as possible)
4. When nosewheel touches down, maintain full up elevator as
airplane slows to stop.
3-16
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
ELECTRICAL
POWER
MALFUNCTIONS
SUPPLY
SYSTEM
HIGH VOLTS ANNUNCIATOR COMES ON OR M BATT
AMPS MORE THAN 40
1. MASTER Switch (ALT Only) - OFF
2. Electrical Load - REDUCE IMMEDIATELY as follows:
a. AVIONICS Switch (BUS 1) - OFF
b. PITOT HEAT Switch - OFF
c. BEACON Light Switch - OFF
d. LAND Light Switch - OFF (use as required for landing)
e. TAXI Light Switch - OFF
f. NAV Light Switch - OFF
g. STROBE Light Switch - OFF
h. CABIN PWR 12V Switch - OFF
NOTE
•
The main battery supplies electrical power to the main
and essential buses until M BUS VOLTS decreases
below 20 volts. When M BUS VOLTS falls below 20
volts, the standby battery system will automatically
supply electrical power to the essential bus for at least
30 minutes.
•
Select COM1 MIC and NAV1 on the audio panel and
tune to the active frequency before setting AVIONICS
BUS 2 to OFF. If COM2 MIC and NAV2 are selected
when AVIONICS BUS 2 is set to OFF, the COM and NAV
radios cannot be tuned.
(Continued Next Page)
172RPHBUS-00
U.S.
3-17
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ELECTRICAL
POWER
MALFUNCTIONS (Continued)
SUPPLY
SYSTEM
HIGH VOLTS ANNUNCIATOR COMES ON OR M BATT
AMPS MORE THAN 40 (Continued)
i.
j.
COM1 and NAV1 - TUNE TO ACTIVE FREQUENCY
COM1 MIC and NAV1 - SELECT (COM2 MIC and NAV2 will
be inoperative once AVIONICS BUS 2 is selected to OFF)
NOTE
When AVIONICS BUS 2 is set to OFF, the following items
will not operate:
Autopilot
COMM 2
Transponder
Audio Panel
NAV 2
MFD
k. AVIONICS Switch (BUS 2) - OFF (KEEP ON if in clouds)
3. Land as soon as practical.
NOTE
Make sure a s uccessf ul landing is possible before
extending flaps. The flap motor is a large electrical load
during operation.
(Continued Next Page)
3-18
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
ELECTRICAL
POWER
MALFUNCTIONS (Continued)
SUPPLY
SYSTEM
LOW VOLTS ANNUNCIATOR COMES ON BELOW 1000
RPM
1. Throttle Control - 1000 RPM
2. LOW VOLTS Annunciator - CHECK OFF
LOW VOLTS ANNUNCIATOR REMAINS ON AT 1000 RPM
3. Authorized maintenance personnel must do electrical system
inspection prior to next flight.
LOW VOLTS ANNUNCIATOR COMES ON OR DOES NOT
GO OFF AT HIGHER RPM
1.
2.
3.
4.
5.
6.
MASTER Switch (ALT Only) - OFF
ALT FIELD Circuit Breaker - CHECK IN
MASTER Switch (ALT and BAT) - ON
LOW VOLTS Annunciator - CHECK OFF
M BUS VOLTS - CHECK 27.5 V (minimum)
M BATT AMPS - CHECK CHARGING (+)
IF LOW VOLTS ANNUNCIATOR REMAINS ON
7. MASTER Switch (ALT Only) - OFF
8. Electrical Load - REDUCE IMMEDIATELY as follows:
a. AVIONICS Switch (BUS 1) - OFF
b. PITOT HEAT Switch - OFF
c. BEACON Light Switch - OFF
d. LAND Light Switch - OFF (use as required for landing)
e. TAXI Light Switch - OFF
f. NAV Light Switch - OFF
g. STROBE Light Switch - OFF
h. CABIN PWR 12V Switch - OFF
(Continued Next Page)
172RPHBUS-00
U.S.
3-19
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS
(Continued)
IF LOW VOLTS ANNUNCIATOR REMAINS ON (Continued)
NOTE
•
•
The main battery supplies electrical power to the main
and essential buses until M BUS VOLTS decreases
below 20 volts. When M BUS VOLTS falls below 20
volts, the standby battery system will automatically
supply electrical power to the essential bus for at least
30 minutes.
Select COM1 MIC and NAV1 on the audio panel and
tune to the active frequency before setting AVIONICS
BUS 2 to OFF. If COM2 MIC and NAV2 are selected
when AVIONICS BUS 2 is set to OFF, the COM and NAV
radios cannot be tuned.
i. COM1 and NAV1 - TUNE TO ACTIVE FREQUENCY
j. COM1 MIC and NAV1 - SELECT (COM2 MIC and NAV2 will
be inoperative once AVIONICS BUS 2 is selected to OFF)
NOTE
When AVIONICS BUS 2 is set to OFF, the following items
will not operate:
Autopilot
COMM 2
Transponder
Audio Panel
NAV 2
MFD
k. AVIONICS Switch (BUS 2) - OFF (KEEP ON if in clouds)
9. Land as soon as practical.
NOTE
Make sure a s uccessf ul landing is possible before
extending flaps. The flap motor is a large electrical load
during operation.
3-20
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
AIR DATA SYSTEM FAILURE
RED X - PFD AIRSPEED INDICATOR
1. ADC/AHRS Circuit Breakers - CHECK IN (ESS BUS and AVN
BUS 1). If open, reset (close) circuit breaker. If circuit breaker
opens again, do not reset.
2. Standby Airspeed Indicator - USE FOR AIRSPEED
INFORMATION
RED X - PFD ALTITUDE INDICATOR
1. ADC/AHRS Circuit Breakers - CHECK IN (ESS BUS and AVN
BUS 1). If open, reset (close) circuit breaker. If circuit breaker
opens again, do not reset.
2. Standby Altimeter - CHECK current barometric pressure SET.
USE FOR ALTITUDE INFORMATION.
ATTITUDE AND HEADING REFERENCE SYSTEM
(AHRS) FAILURE
RED X - PFD ATTITUDE INDICATOR
1. ADC/AHRS Circuit Breakers - CHECK IN (ESS BUS and AVN
BUS 1). If open, reset (close) circuit breaker. If circuit breaker
opens again, do not reset.
2. Standby Attitude Indicator - USE FOR ATTITUDE
INFORMATION
RED X - HORIZONTAL SITUATION INDICATOR (HSI)
1. ADC/AHRS Circuit Breakers - CHECK IN (ESS BUS and AVN
BUS 1). If open, reset (close) circuit breaker. If circuit breaker
opens again, do not reset.
2. Non-Stabilized Magnetic Compass - USE FOR HEADING
INFORMATION
172RPHBUS-00
U.S.
3-21
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AUTOPILOT OR ELECTRIC TRIM FAILURE (if installed)
AP OR PTRM ANNUNCIATOR(S) COME ON
1. Control Wheel - GRASP FIRMLY (regain control of airplane)
2. A/P TRIM DISC Button - PRESS and HOLD (throughout
recovery)
3. Elevator Control - ADJUST MANUALLY (as necessary)
4. AUTO PILOT Circuit Breaker - OPEN (pull out)
5. A/P TRIM DISC Button - RELEASE
WARNING
FOLLOWING AN AUTOPILOT, AUTOTRIM OR MANUAL
ELECTRIC TRIM SYSTEM MALFUNCTION, DO NOT
ENGAGE THE AUTOPILOT UNTIL THE CAUSE OF THE
MALFUNCTION HAS BEEN CORRECTED.
3-22
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
DISPLAY COOLING ADVISORY
PFD1 COOLING OR MFD1 COOLING ANNUNCIATOR(S)
COME ON
1. CABIN HT Control Knob - REDUCE (push in) (minimum
preferred)
2. Forward Avionics Fan - CHECK (feel for airflow from screen on
glareshield)
IF FORWARD AVIONICS FAN HAS FAILED
3. STBY BATT Switch - OFF (unless needed for emergency
power)
IF PFD1 COOLING OR MFD1 COOLING ANNUNCIATOR DOES
NOT GO OFF WITHIN 3 MINUTES OR IF BOTH PFD1 COOLING
AND MFD1 COOLING ANNUNCIATORS COME ON
3. STBY BATT Switch - OFF (land as soon as practical)
VACUUM SYSTEM FAILURE
LOW VACUUM ANNUNCIATOR COMES ON
1. Vacuum Indicator (VAC) - CHECK EIS ENGINE PAGE (make
sure vacuum pointer is in green band limits)
CAUTION
IF VACUUM POINTER IS OUT OF THE GREEN BAND
DURING FLIGHT OR THE GYRO FLAG IS SHOWN ON
THE STANDBY ATTITUDE INDICATOR, THE STANDBY
ATTITUDE INDICATOR MUST NOT BE USED FOR
ATTITUDE INFORMATION.
172RPHBUS-00
U.S.
3-23
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
HIGH CARBON MONOXIDE (CO) LEVEL ADVISORY
CO LVL HIGH ANNUNCIATOR COMES ON
1.
2.
3.
4.
CABIN HT Control Knob - OFF (push full in)
CABIN AIR Control Knob - ON (pull full out)
Cabin Vents - OPEN
Cabin Windows - OPEN (163 KIAS maximum windows open
speed)
CO LVL HIGH ANNUNCIATOR REMAINS ON
5. Land as soon as practical.
3-24
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
AMPLIFIED EMERGENCY PROCEDURES
The following Amplified Emergency Procedures provide additional
information beyond that in the Emergency Procedures Checklists
portion of this section. These procedures also include information not
readily adaptable to a checklist format, and material to which a pilot
could not be expected to refer in resolution of a specific emergency.
This information should be reviewed in detail prior to flying the airplane,
as well as reviewed on a regular basis to keep pilot’s knowledge of
procedures fresh.
ENGINE FAILURE
If an engine failure occurs during the takeoff roll, stop the airplane on
the remaining runway. Those extra items on the checklist will provide
added safety after a failure of this type.
If an engine failure occurs immediately after takeoff, in most cases, the
landing should be planned straight ahead with only small changes in
direction to avoid obstructions. Altitude and airspeed are seldom
sufficient to execute the 180° gliding turn necessary to return to the
runway. The checklist procedures assume that adequate time exists to
secure the fuel and ignition systems prior to touchdown.
After an engine failure in flight, the most important task is to continue
flying the airplane. The best glide speed, as shown in Figure 3-1,
should be established as quickly as possible. While gliding toward a
suitable landing area, an effort should be made to identify the cause of
the failure. If time permits, an engine restart should be attempted as
shown in the checklist. If the engine cannot be restarted, a forced
landing without power must be completed.
172RPHBUS-00
U.S.
3-25
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
MAXIMUM GLIDE
Figure 3-1
3-26
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
FORCED LANDINGS
If all attempts to restart the engine fail and a forced landing is imminent,
select a suitable field and prepare for the landing as discussed under
the Emergency Landing Without Engine Power checklist. Transmit
Mayday message on 121.5 MHz giving location, intentions and squawk
7700.
Before attempting an off airport landing with engine power available,
one should fly over the landing area at a safe, but low altitude, to
inspect the terrain for obstructions and surface conditions, proceeding
as discussed in the Precautionary Landing With Engine Power
checklist.
Prepare for ditching by securing or jettisoning heavy objects located in
the baggage area and collect folded coats for protection of occupants'
face at touchdown. Transmit Mayday messages on 121.5 MHz giving
location, intentions and squawk 7700. Avoid a landing flare because of
the difficulty in judging height over a water surface. The checklist
assumes the availability of power to make a precautionary water
landing. If power is not available, use of the airspeeds noted with
minimum flap extension will provide a more favorable attitude for a
power off ditching.
In a forced landing situation, do not turn off the MASTER switch,
AVIONICS switch or STBY BATT switch until a landing is assured.
Premature deactivation of the switches will disable all airplane electrical
systems.
Before completing a forced landing, especially in remote and
mountainous areas, activate the ELT by setting the cockpit-mounted
switch to the ON position. For complete information on ELT operation,
refer to Section 9, Supplements.
172RPHBUS-00
U.S.
3-27
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
LANDING WITHOUT ELEVATOR CONTROL
Trim for horizontal flight with an airspeed of approximately 65 KIAS and
flaps set to 20° by using throttle and elevator trim controls. Then do not
change the elevator trim control setting; control the glide angle by
adjusting power.
During the landing flare (round-out), the nose will come down when
power is reduced and the airplane may touch down on the nosewheel
before the main wheels. When in the flare, the elevator trim control
should be adjusted toward the full nose up position and the power
adjusted at the same time so that the airplane will rotate to a horizontal
attitude for touchdown. Close the throttle at touchdown.
FIRES
Improper starting procedures involving the excessive use of auxiliary
fuel pump operation can cause engine flooding and subsequent
collection of fuel on the parking ramp as the excess fuel drains
overboard from the intake manifolds. This is sometimes experienced in
difficult starts in cold weather where engine preheat service is not
available. If this occurs, the airplane should be pushed away from the
fuel puddle before another engine start is attempted. Otherwise, there
is a possibility of raw fuel accumulations in the exhaust system igniting
during an engine start, causing a long flame from the tailpipe, and
possibly igniting the collected fuel on the pavement. If a fire occurs,
proceed according to the checklist.
Although engine fires are extremely rare in flight, if a fire is
encountered, the steps of the appropriate checklist should be followed.
After completion of the checklist procedure, execute a forced landing.
Do not attempt to restart the engine.
The first sign of an electrical fire is usually the smell of burning
insulation. The checklist procedure should result in the elimination of
the fire.
3-28
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
EMERGENCY OPERATION IN CLOUDS
If the engine-driven vacuum pump fails in flight, the standby attitude
indicator will not be accurate. The pilot must then rely on the attitude
and heading information (from the AHRS) shown on the PFD
indicators. With valid HDG or GPS/NAV inputs, autopilot operation will
not be affected.
If the AHRS unit fails in flight (red X’s shown through the PFD attitude
and heading indicators), the pilot must rely on the standby attitude
indicator and non-stabilized magnetic compass for attitude and heading
information.
The autopilot will not operate if the AHRS unit fails. The pilot must
manually fly the airplane without AHRS input. Refer to Section 7,
Airplane and Systems Description, for additional details on autopilot
operations.
The following instructions assume that the pilot is not very proficient at
instrument flying and is flying the airplane without the autopilot
engaged.
EXECUTING A 180° TURN IN CLOUDS (AHRS FAILED)
Upon inadvertently entering the clouds, an immediate turn to reverse
course and return to VFR conditions should be made as follows:
AHRS FAILURE
1. Note the non-stabilized magnetic compass heading.
2. Using the standby attitude indicator, initiate a 15° bank left turn.
Keep feet off rudder pedals. Maintain altitude and 15° bank
angle. Continue the turn for 60 seconds, then roll back to level
flight.
3. When the compass card becomes sufficiently stable, check the
accuracy of the turn by verifying that the compass heading
approximates the reciprocal of the original heading.
4. If necessary, adjust the heading by keeping the wings level and
using the rudder to make skidding turns (the compass will read
more accurately) to complete the course reversal.
5. Maintain altitude and airspeed by cautious application of
elevator control. Keep the roll pointer and index aligned and
steer only with rudder.
(Continued Next Page)
172RPHBUS-00
U.S.
3-29
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
EMERGENCY OPERATION IN CLOUDS (Continued)
EMERGENCY DESCENT THROUGH CLOUDS (AHRS
FAILED)
When returning to VFR flight after a 180° turn is not practical, a descent
through the clouds to VFR conditions below may be appropriate. If
possible, obtain an ATC clearance for an emergency descent through
the clouds.
AHRS FAILURE
Choose an easterly or westerly heading to minimize non-stabilized
magnetic compass card sensitivity. Occasionally check the compass
heading and make minor corrections to hold an approximate course.
The autopilot will not operate if the AHRS unit fails. The pilot must
manually fly the airplane without AHRS input.
Before descending into the clouds, prepare for a stabilized descent as
follows:
1. Apply full rich mixture.
2. Turn pitot heat on.
3. Set power for a 500 to 800 feet per minute rate of descent.
4. Set the elevator trim for a stabilized descent at 70-80 KIAS.
5. Use the standby attitude indicator roll pointer and index to keep
wings level.
6. Check trend of compass card movement and make cautious
corrections with rudder to stop the turn.
7. Upon breaking out of clouds, resume normal cruising flight.
(Continued Next Page)
3-30
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
EMERGENCY OPERATION IN CLOUDS (Continued)
RECOVERY FROM SPIRAL DIVE IN THE CLOUDS (AHRS
FAILED)
AHRS FAILURE
If a spiral is entered while in the clouds, continue as follows:
1. Retard throttle to idle position.
2. Remove feet from rudder pedals.
3. Stop turn by carefully leveling the wings using aileron control to
align the roll index and roll pointer of the standby attitude
indicator.
4. Cautiously apply elevator back pressure to slowly reduce the
airspeed to 80 KIAS.
5. Adjust the elevator trim control to maintain an 80 KIAS glide.
6. Use aileron control to maintain wings level (keep roll pointer and
index aligned) and constant heading.
7. Resume Emergency Descent Through The Clouds procedure.
8. Upon breaking out of clouds, resume normal cruising flight.
INADVERTENT FLIGHT INTO ICING CONDITIONS
Flight into icing conditions is prohibited and extremely dangerous. An
inadvertent encounter with these conditions can be resolved using the
checklist procedures. The best action is to turn back or change altitude
to escape icing conditions. Set the PITOT HEAT switch to the ON
position until safely out of icing conditions.
During these encounters, an unexplained loss of engine power could
be caused by ice blocking the air intake filter or in extremely rare
instances ice completely blocking the fuel injection air reference tubes.
In either case, the throttle should be positioned to obtain maximum
RPM (in some instances, the throttle may need to be retarded for
maximum power). The mixture should then be adjusted, as required, to
obtain maximum RPM.
172RPHBUS-00
U.S.
3-31
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
STATIC SOURCE BLOCKED
If erroneous readings of the static source instruments (airspeed,
altimeter and vertical speed) are suspected, the alternate static source
air valve (ALT STATIC AIR) should be pulled ON, thereby supplying
static pressure to these instruments from the cabin.
When the ALT STATIC AIR valve is ON, the maximum airspeed
variation from normal static source operation is 6 knots and the
maximum altimeter variation is 50 feet with all windows closed. Refer to
Section 5, Figure 5-1 (Sheet 2), Airspeed Calibration - Alternate Static
Source correction tables for additional details.
SPINS
Should an inadvertent spin occur, the following recovery procedure
should be used:
1. RETARD THROTTLE TO IDLE POSITION.
2. PLACE AILERONS IN NEUTRAL POSITION.
3. APPLY AND HOLD FULL RUDDER OPPOSITE TO THE
DIRECTION OF ROTATION.
4. JUST AFTER THE RUDDER REACHES THE STOP, MOVE
THE CONTROL WHEEL BRISKLY FORWARD FAR ENOUGH
TO BREAK THE STALL. Full down elevator may be required at
aft center of gravity loadings to assure optimum recoveries.
5. HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS.
Premature relaxation of the control inputs may extend the
recovery.
6. AS ROTATION STOPS, NEUTRALIZE RUDDER, AND MAKE A
SMOOTH RECOVERY FROM THE RESULTING DIVE.
NOTE
If the rate of the spin makes determining the direction of
rotation difficult, the magenta turn rate indicator at the top of
the HSI compass card will show the rate and direction of
the turn. The HSI compass card will rotate in the opposite
direction. Hold opposite rudder to the turn vector direction.
For additional information on spins and spin recovery, see the
discussion under SPINS in Normal Procedures, Section 4.
3-32
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
ROUGH ENGINE OPERATION OR LOSS OF POWER
SPARK PLUG FOULING
A slight engine roughness in flight may be caused by one or more spark
plugs becoming fouled by carbon or lead deposits. This may be verified
by turning the MAGNETOS switch momentarily from BOTH to either L
or R position. An obvious power loss in single magneto operation is
evidence of spark plug or magneto trouble. Since spark plugs are the
more likely cause, lean the mixture to the recommended lean setting for
cruising flight. If the problem does not clear up in several minutes,
determine if a richer mixture setting will produce smoother operation. If
not, proceed to the nearest airport for repairs using the BOTH position
of the MAGNETOS switch unless extreme roughness makes the use of
a single MAGNETO position necessary.
MAGNETO MALFUNCTION
Sudden engine roughness or misfiring is usually a sign of a magneto
problem. Changing the MAGNETOS switch from BOTH to the L and R
switch positions will identify which magneto is malfunctioning. Select
different power settings and enrichen the mixture to determine if
continued operation on BOTH magnetos is possible. If not, change to
the good magneto and continue to the nearest airport for repairs.
IDLE POWER ENGINE ROUGHNESS
(As Required by AD 2001-06-17, Paragraph (d)(3))
An excessively rich idle fuel flow may cause low speed engine
roughness during flight. During most in-flight low engine speeds (power
off stalls, approach to landing, etc.), the mixture control is normally in
the full-rich position. However, to improve engine roughness (caused
by an improperly adjusted fuel servo) during low engine speeds while in
flight, you should rotate the vernier mixture control (leaning of fuel
mixture). You may also have to lean the fuel mixture if this low engine
speed results in power loss and you need to restart the engine during
flight. In all cases, you should land the airplane at the nearest airport for
repairs if low speed engine roughness requires you to adjust the fuel
mixture control to improve engine operation.
(Continued Next Page)
172RPHBUS-00
U.S.
3-33
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ROUGH ENGINE OPERATION OR LOSS OF POWER
(Continued)
ENGINE-DRIVEN FUEL PUMP FAILURE
Failure of the engine-driven fuel pump will be shown by a sudden
reduction in the fuel flow indication (FFLOW GPH) immediately before
a loss of power while operating from a fuel tank containing adequate
fuel.
If the engine-driven fuel pump fails, immediately set the FUEL PUMP
switch to the ON position to restore the engine power. The flight should
be terminated as soon as practical and the engine-driven fuel pump
repaired.
EXCESSIVE FUEL VAPOR
Fuel vapor in the fuel injection system is most likely to occur on the
ground, typically during prolonged taxi operations, when operating at
higher altitudes and/or in unusually warm temperatures.
Excessive fuel vapor accumulation is shown by fuel flow indicator
(FFLOW GPH) fluctuations greater than 1 gal./hr. This condition, with
leaner mixtures or with larger fluctuations, can result in power surges,
and if not corrected, may cause power loss.
To slow vapor formation and stabilize fuel flow on the ground or in the
air, set the FUEL PUMP switch to the ON position and adjust the
mixture as required for smooth engine operation. If vapor symptoms
continue, select the opposite fuel tank. When fuel flow stabilizes, set
the FUEL PUMP switch to the OFF position and adjust the mixture as
desired.
(Continued Next Page)
3-34
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
ROUGH ENGINE OPERATION OR LOSS OF POWER
(Continued)
LOW OIL PRESSURE
If the low oil pressure annunciator (OIL PRESS) comes on, check the
oil pressure indicator (OIL PRES on ENGINE page or OIL PSI on
SYSTEM page) to confirm low oil pressure condition. If oil pressure and
oil temperature (OIL TEMP on ENGINE page or OIL °F on SYSTEM
page) remain normal, it is possible that the oil pressure sending unit or
relief valve is malfunctioning. Land at the nearest airport to determine
the source of the problem.
If a total loss of oil pressure and a rise in oil temperature occur at about
the same time, it could mean that the engine is about to fail. Reduce
power immediately and select a field suitable for a forced landing. Use
only the minimum power necessary to reach the landing site.
172RPHBUS-00
U.S.
3-35
SECTION 3
EMERGENCY PROCEDURES
ELECTRICAL
POWER
MALFUNCTIONS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SUPPLY
SYSTEM
Malfunctions in the electrical power supply system can be detected
through regular monitoring of the main battery ammeter (M BATT
AMPS) and the main electrical bus voltmeter (M BUS VOLTS);
however, the cause of these malfunctions is usually difficult to
determine. A broken alternator drive belt, too much wear on the
alternator brushes, or an error in wiring is most likely the cause of
alternator failures, although other factors could cause the problem. A
defective Alternator Control Unit (ACU) can also cause malfunctions.
Problems of this nature constitute an electrical emergency and should
be dealt with immediately. Electrical power malfunctions usually fall into
two categories: excessive rate of charge and insufficient rate of charge.
The following paragraphs describe the recommended remedy for each
situation.
EXCESSIVE RATE OF CHARGE
After engine starting and heavy electrical usage at low engine speeds
(such as extended taxiing), the battery condition will be low enough to
accept above normal charging during the initial part of a flight.
However, after thirty minutes of cruising flight, the main battery
ammeter (M BATT AMPS) should be indicating less than 5 amps of
charging (+) current. If the charging current remains above this value
on a long flight, the battery electrolyte could overheat and evaporate.
Electronic components in the electrical system can be adversely
affected by higher than normal voltage. The ACU includes an
overvoltage sensor circuit which will automatically disconnect the
alternator if the charge voltage increases to more than approximately
31.75 volts. If the overvoltage sensor circuit does not operate correctly,
as shown by voltage more than 31.75 volts on the main battery bus
voltmeter, the MASTER switch ALT section should be set to the OFF
position. Unnecessary electrical equipment should be de-energized
and the flight terminated as soon as practical.
(Continued Next Page)
3-36
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 3
EMERGENCY PROCEDURES
ELECTRICAL
POWER
MALFUNCTIONS (Continued)
SUPPLY
SYSTEM
INSUFFICIENT RATE OF CHARGE
When the overvoltage sensor circuit, or other fault, opens the alternator
(ALT FIELD) circuit breaker and de-energizes the alternator, a
discharge (-) current will be shown on the main battery ammeter and
the low voltage annunciator (LOW VOLTS) will come on. The ACU can
de-energize the alternator due to minor disturbances in the electrical
system, resulting in a nuisance opening of the ALT FIELD circuit
breaker. If this happens, an attempt should be made to energize the
alternator system.
To energize the alternator system
1. MASTER Switch (ALT Only) - OFF
2. ALT FIELD Circuit Breaker - CHECK IN
3. MASTER Switch (ALT Only) - ON
If the problem was a minor ACU disturbance in the electrical system,
normal main battery charging will start. A charge (+) current will be
shown on the main battery ammeter and the LOW VOLTS annunciator
will go off.
If the LOW VOLTS annunciator comes on again, there is an alternator
system problem. Do not repeat steps to energize the alternator system.
The electrical load on the battery must be minimized (by de-energizing
nonessential electrical equipment and avionics) because the battery
can supply the electrical system for only a short time. Reduce electrical
load as soon as possible to extend the life of the battery for landing.
Land as soon as practical.
(Continued Next Page)
172RPHBUS-00
U.S.
3-37
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ELECTRICAL
POWER
MALFUNCTIONS (Continued)
SUPPLY
SYSTEM
INSUFFICIENT RATE OF CHARGE (Continued)
Main battery life can be extended by setting the MASTER switch (ALT
and BAT) to OFF and operating the equipment on the ESS BUS from
the standby battery. The standby battery is only capable of providing
power for systems on the essential bus and cannot provide power for
transponder (XPDR) operation. Main battery life should be extended,
when practical, for possible later operation of the wing flaps and use of
the landing light (at night).
NOTE
The LOW VOLTS annunciator can come on when the
engine is operated at low RPM with a high electrical load.
The LOW VOLTS annunciator will usually go off when the
engine is operated at higher RPM for greater alternator
sy stem out put . Make sure that t he M BATT AMPS
indication shows positive (+) current at the higher RPM.
3-38
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
HIGH
CARBON
ANNUNCIATION
SECTION 3
EMERGENCY PROCEDURES
MONOXIDE
(CO)
LEVEL
Carbon monoxide (CO) is a colorless, odorless, tasteless product of an
internal combustion engine and is always present in exhaust fumes.
Even minute quantities of carbon monoxide breathed over a long
period of time may lead to dire consequences. The symptoms of
carbon monoxide poisoning are difficult to detect by the person affected
and may include blurred thinking, a feeling of uneasiness, dizziness,
headache, and loss of consciousness.
The cabin heater system operates by allowing ambient air to flow
through an exhaust shroud where it is heated before being ducted into
the cabin. If an exhaust leak, caused by a crack in the exhaust pipe,
occurs in the area surrounded by this shroud it would allow exhaust
fumes to mix with the heated ambient air being ducted into the cabin.
Therefore, if anyone in the cabin smells exhaust fumes, experiences
any of the symptoms mentioned above, or the CO LVL HIGH warning
annunciation comes on when using the cabin heater, immediately turn
off the cabin heater and preform the emergency items for High Carbon
Monoxide (CO) Level Advisory.
When the CO detection system senses a CO level of 50 parts per
million (PPM) by volume or greater, the alarm turns on a flashing
warning annunciation CO LVL HIGH in the annunciation window on the
PFD with a continuous tone until the PFD softkey below WARNING is
pushed. It then remains on steady until the CO level drops below 50
PPM and automatically resets the alarm.
OTHER EMERGENCIES
WINDSHIELD DAMAGE
If a bird strike or other incident should damage the windshield in flight to
the point of creating an opening, a significant loss in performance may
be expected. This loss may be minimized in some cases (depending on
amount of damage, altitude, etc.) by opening the side windows while
the airplane is maneuvered for a landing at the nearest airport. If
airplane performance or other adverse conditions prevent landing at an
airport, prepare for an off airport landing in accordance with the
Precautionary Landing With Engine Power or Ditching checklists.
172RPHBUS-00
U.S.
3-39/3-40
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
NORMAL PROCEDURES
TABLE OF CONTENTS
Page
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-3
Airspeeds For Normal Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-3
NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-4
Preflight Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-4
Cabin. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-5
Empennage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6
Right Wing Trailing Edge. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6
Right Wing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-7
Nose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-8
Left Wing Leading Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9
Left Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-10
Left Wing Trailing Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-10
Before Starting Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-11
Starting Engine (With Battery) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-12
Starting Engine (With External Power) . . . . . . . . . . . . . . . . . . . . . . 4-13
Before Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-15
Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-18
Normal Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-18
Short Field Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-18
Enroute Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-19
Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-19
Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-20
Before Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-21
Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-21
Normal Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-21
Short Field Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-21
Balked Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-22
After Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-22
Securing Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-22
(Continued Next Page)
172RPHBUS-00
U.S.
4-1
SECTION 4
NORMAL PROCEDURES
TABLE OF CONTENTS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
(Continued)
Page
AMPLIFIED NORMAL PROCEDURES. . . . . . . . . . . . . . . . . . . . .
Preflight Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Starting Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Recommended Starter Duty Cycle . . . . . . . . . . . . . . . . . . . . . .
Leaning For Ground Operations. . . . . . . . . . . . . . . . . . . . . . . . . . .
Taxiing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Before Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Warm Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Magneto Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Alternator Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Elevator Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Power Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Wing Flap Settings. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Crosswind Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Enroute Climb. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Leaning Using Exhaust Gas Temperature (EGT) . . . . . . . . . . .
Fuel Savings Procedures For Flight Training Operations . . . . .
Fuel Vapor Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Stalls. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Spins. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Normal Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Short Field Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Crosswind Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Balked Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Cold Weather Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Starting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Winterization Kit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Hot Weather Operations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Noise Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-2
U.S.
4-23
4-23
4-25
4-26
4-26
4-27
4-29
4-29
4-29
4-29
4-30
4-30
4-30
4-30
4-31
4-31
4-32
4-33
4-35
4-38
4-39
4-40
4-40
4-43
4-43
4-43
4-44
4-44
4-45
4-46
4-47
4-48
4-48
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
INTRODUCTION
Section 4 provides procedures and amplified instructions for normal
operations using standard equipment. Normal procedures associated
with optional systems can be found in Section 9, Supplements.
AIRSPEEDS FOR NORMAL OPERATION
Unless otherwise noted, the following speeds are based on a maximum
weight of 2450 pounds and may be used for any lesser weight.
TAKEOFF
Normal Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70 - 80 KIAS
Short Field Takeoff, Flaps 10°, Speed at 50 Feet . . . . . . . . . 57 KIAS
ENROUTE CLIMB, FLAPS UP
Normal, Sea Level. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75 - 85 KIAS
Normal, 10,000 Feet . . . . . . . . . . . . . . . . . . . . . . . . . . . 70 - 80 KIAS
Best Rate of Climb, Sea Level . . . . . . . . . . . . . . . . . . . . . . . 79 KIAS
Best Rate of Climb, 10,000 Feet . . . . . . . . . . . . . . . . . . . . . . 71 KIAS
Best Angle of Climb, Sea Level. . . . . . . . . . . . . . . . . . . . . . . 60 KIAS
Best Angle of Climb, 10,000 Feet . . . . . . . . . . . . . . . . . . . . . 65 KIAS
LANDING APPROACH
Normal Approach, Flaps UP . . . . . . . . . . . . . . . . . . . . . 65 - 75 KIAS
Normal Approach, Flaps FULL . . . . . . . . . . . . . . . . . . . 60 - 70 KIAS
Short Field Approach, Flaps FULL . . . . . . . . . . . . . . . . . . . . 62 KIAS
BALKED LANDING
Maximum Power, Flaps 20° . . . . . . . . . . . . . . . . . . . . . . . . . 55 KIAS
MAXIMUM
RECOMMENDED
PENETRATION SPEED
TURBULENT
AIR
2450 POUNDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99 KIAS
2200 POUNDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94 KIAS
1600 POUNDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 KIAS
MAXIMUM DEMONSTRATED CROSSWIND VELOCITY
Takeoff or Landing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15 KNOTS
172RPHBUS-00
U.S.
4-3
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
NORMAL PROCEDURES
PREFLIGHT INSPECTION
NOTE
Visually check airplane for general condition during walkaround inspection. Airplane should be parked in a normal
ground attitude (refer to Figure 1-1) to make sure that fuel
drain valves allow for accurate sampling. Use of the
refueling steps and assist handles will simplify access to
the upper wing surfaces for visual checks and refueling
o p e r a t i o n s . I n c o l d w e a t h e r, r e m o v e e v e n s m a l l
accumulations of frost, ice or snow from wing, tail and
control surfaces. Also, make sure that control surfaces
contain no internal accumulations of ice or debris. Prior to
flight, check that pitot heater is warm to touch within 30
seconds with battery and pitot heat switches on. If a night
flight is planned, check operation of all lights, and make
sure a flashlight is available.
Figure 4-1
4-4
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
PREFLIGHT INSPECTION (Continued)
1
CABIN
1. Pitot Tube Cover - REMOVE (check for pitot blockage)
2. Pilot's Operating Handbook - ACCESSIBLE TO PILOT
3. Garmin G1000 Cockpit Reference Guide - ACCESSIBLE TO
PILOT
4. Airplane Weight and Balance - CHECKED
5. Parking Brake - SET
6. Control Wheel Lock - REMOVE
WARNING
WHEN THE MASTER SWITCH IS ON, USING AN
EXTERNAL POWER SOURCE, OR MANUALLY
ROTATING THE PROPELLER, TREAT THE PROPELLER
AS IF THE MAGNETOS SWITCH WERE ON. DO NOT
STAND, NOR ALLOW ANYONE ELSE TO STAND,
WITHIN THE ARC OF THE PROPELLER SINCE A
LOOSE OR BROKEN WIRE, OR A COMPONENT
MALFUNCTION, COULD CAUSE THE ENGINE TO
START.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
MAGNETOS Switch - OFF
AVIONICS Switch (BUS 1 and BUS 2) - OFF
MASTER Switch (ALT and BAT) - ON
Primary Flight Display (PFD) - CHECK (verify PFD is ON)
FUEL QTY (L and R) - CHECK
LOW FUEL L and LOW FUEL R Annunciators - CHECK (verify
annunciators are not shown on PFD)
OIL PRESSURE Annunciator - CHECK (verify annunciator is
shown)
LOW VACUUM Annunciator - CHECK (verify annunciator is
shown)
AVIONICS Switch (BUS 1) - ON
Forward Avionics Fan - CHECK (verify fan is heard)
(Continued Next Page)
172RPHBUS-00
U.S.
4-5
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PREFLIGHT INSPECTION (Continued)
1
CABIN (Continued)
17.
18.
19.
20.
21.
22.
23.
24.
25.
26.
27.
28.
2
AVIONICS Switch (BUS 1) - OFF
AVIONICS Switch (BUS 2) - ON
Aft Avionics Fan - CHECK (verify fan is heard)
AVIONICS Switch (BUS 2) - OFF
PITOT HEAT Switch - ON (carefully check that pitot tube is
warm to the touch within 30 seconds)
PITOT HEAT Switch - OFF
LOW VOLTS Annunciator - CHECK (verify annunciator is
shown)
MASTER Switch (ALT and BAT) - OFF
Elevator Trim Control - TAKEOFF position
FUEL SELECTOR Valve - BOTH
ALT STATIC AIR Valve - OFF (push full in)
Fire Extinguisher - CHECK (verify gage pointer in green arc)
EMPENNAGE
1. Baggage Compartment Door - CHECK (lock with key)
2. Rudder Gust Lock (if installed) - REMOVE
3. Tail Tiedown - DISCONNECT
4. Control Surfaces - CHECK (freedom of movement and security)
5. Elevator Trim Tab - CHECK (security)
6. Antennas - CHECK (security of attachment and general
condition)
3 RIGHT WING Trailing Edge
1. Flap - CHECK (security and condition)
2. Aileron - CHECK (freedom of movement and security)
(Continued Next Page)
4-6
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
PREFLIGHT INSPECTION (Continued)
4
RIGHT WING
1. Wing Tiedown - DISCONNECT
2. Main Wheel Tire - CHECK (proper inflation and general
condition (weather checks, tread depth and wear, etc.))
3. Fuel Tank Sump Quick Drain Valves - DRAIN
Drain at least a cupful of fuel (using sampler cup) from each
sump location to check for water, sediment, and proper fuel
grade before each flight and after each refueling. If water is
observed, take further samples until clear and then gently rock
wings and lower tail to the ground to move any additional
contaminants to the sampling points. Take repeated samples
from all fuel drain points until all contamination has been
removed. If contaminants are still present, refer to WARNING
below and do not fly airplane.
NOTE
Collect all sampled fuel in a safe container. Dispose of the
sampled fuel so that it does not cause a nuisance, hazard
or damage to the environment.
WARNING
IF, AFTER REPEATED SAMPLING, EVIDENCE OF
CONTAMINATION STILL EXISTS, THE AIRPLANE
SHOULD NOT BE FLOWN. TANKS SHOULD BE
DRAINED AND SYSTEM PURGED BY QUALIFIED
MAINTENANCE PERSONNEL. ALL EVIDENCE OF
CONTAMINATION MUST BE REMOVED BEFORE
FURTHER FLIGHT.
4. Fuel Quantity - CHECK VISUALLY (for desired level)
5. Fuel Filler Cap - SECURE and VENT CLEAR
(Continued Next Page)
172RPHBUS-00
U.S.
4-7
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PREFLIGHT INSPECTION (Continued)
5
NOSE
1. Fuel Strainer Quick Drain Valve (located on bottom of fuselage) DRAIN
Drain at least a cupful of fuel (using sampler cup) from valve to
check for water, sediment, and proper fuel grade before each
flight and after each refueling. If water is observed, take further
samples until clear and then gently rock wings and lower tail to
the ground to move any additional contaminants to the sampling
points. Take repeated samples from all fuel drain points,
including the fuel reservoir and fuel selector, until all
contamination has been removed. If contaminants are still
present, refer to WARNING below and do not fly the airplane.
NOTE
Collect all sampled fuel in a safe container. Dispose of the
sampled fuel so that it does not cause a nuisance, hazard,
or damage to the environment.
WARNING
IF, AFTER REPEATED SAMPLING, EVIDENCE OF
CONTAMINATION STILL EXISTS, THE AIRPLANE
SHOULD NOT BE FLOWN. TANKS SHOULD BE
DRAINED AND SYSTEM PURGED BY QUALIFIED
MAINTENANCE PERSONNEL. ALL EVIDENCE OF
CONTAMINATION MUST BE REMOVED BEFORE
FURTHER FLIGHT.
2. Engine Oil Dipstick/Filler Cap:
a. Oil level - CHECK
b. Dipstick/filler cap - SECURE
NOTE
Do not operate with less than 5 quarts. Fill to 8 quarts for
extended flight.
(Continued Next Page)
4-8
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
PREFLIGHT INSPECTION (Continued)
5
NOSE (Continued)
3. Engine Cooling Air Inlets - CHECK (clear of obstructions)
4. Propeller and Spinner - CHECK (for nicks and security)
5. Air Filter - CHECK (for restrictions by dust or other foreign
matter)
6. Nosewheel Strut and Tire - CHECK (proper inflation of strut and
general condition of tire (weather checks, tread depth and wear,
etc.))
7. Static Source Opening (left side of fuselage) - CHECK (verify
opening is clear)
6
LEFT WING Leading Edge
1. Fuel Tank Vent Opening - CHECK (blockage)
2. Stall Warning Opening - CHECK (blockage)
NOTE
To check the system, place a clean handkerchief over the
vent opening and apply suction; a sound from the warning
horn will confirm system operation.
3. Landing/Taxi Light(s) - CHECK (condition and cleanliness of
cover)
(Continued Next Page)
172RPHBUS-00
U.S.
4-9
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PREFLIGHT INSPECTION (Continued)
7
LEFT WING
1. Wing Tiedown - DISCONNECT
2. Fuel Quantity - CHECK VISUALLY (for desired level)
3. Fuel Filler Cap - SECURE and VENT CLEAR
4. Fuel Tank Sump Quick Drain Valves - DRAIN
Drain at least a cupful of fuel (using sampler cup) from each
sump location to check for water, sediment, and proper fuel
grade before each flight and after each refueling. If water is
observed, take further samples until clear and then gently rock
wings and lower tail to the ground to move any additional
contaminants to the sampling points. Take repeated samples
from all fuel drain points until all contamination has been
removed. If contaminants are still present, refer to WARNING
below and do not fly airplane.
NOTE
Collect all sampled fuel in a safe container. Dispose of the
sampled fuel so that it does not cause a nuisance, hazard,
or damage to the environment.
WARNING
IF, AFTER REPEATED SAMPLING, EVIDENCE OF
CONTAMINATION STILL EXISTS, THE AIRPLANE
SHOULD NOT BE FLOWN. TANKS SHOULD BE
DRAINED AND SYSTEM PURGED BY QUALIFIED
MAINTENANCE PERSONNEL. ALL EVIDENCE OF
CONTAMINATION MUST BE REMOVED BEFORE
FURTHER FLIGHT.
5. Main Wheel Tire - CHECK (proper inflation and general
condition (weather checks, tread depth and wear, etc.))
8
LEFT WING Trailing Edge
1. Aileron - CHECK (freedom of movement and security)
2. Flap - CHECK (security and condition)
4-10
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
BEFORE STARTING ENGINE
1. Preflight Inspection - COMPLETE
2. Passenger Briefing - COMPLETE
3. Seats and Seat Belts - ADJUST and LOCK (verify inertia reel
locking)
4. Brakes - TEST and SET
5. Circuit Breakers - CHECK IN
6. Electrical Equipment - OFF
7. AVIONICS Switch (BUS 1 and BUS 2) - OFF
CAUTION
THE AVIONICS SWITCH (BUS 1 AND BUS 2) MUST BE
OFF DURING ENGINE START TO PREVENT POSSIBLE
DAMAGE TO AVIONICS.
8. FUEL SELECTOR Valve - BOTH
9. FUEL SHUTOFF Valve - ON (push full in)
172RPHBUS-00
U.S.
4-11
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
STARTING ENGINE (With Battery)
1. Throttle Control - OPEN 1/4 INCH
2. Mixture Control - IDLE CUTOFF (pull full out)
3. STBY BATT Switch:
a. TEST - (hold for 20 seconds, verify that green TEST lamp
does not go off)
b. ARM - (verify that PFD comes on)
4. Engine Indicating System - CHECK PARAMETERS (verify no
red X's through ENGINE page indicators)
5. BUS E Volts - CHECK (verify 24 VOLTS minimum shown)
6. M BUS Volts - CHECK (verify 1.5 VOLTS or less shown)
7. BATT S Amps - CHECK (verify discharge shown (negative))
8. STBY BATT Annunciator - CHECK (verify annunciator is shown)
9. Propeller Area - CLEAR (verify that all people and equipment
are at a safe distance from the propeller)
10. MASTER Switch (ALT and BAT) - ON
11. BEACON Light Switch - ON
NOTE
If engine is warm, omit priming procedure steps 12 thru 14
below.
12. FUEL PUMP Switch - ON
13. Mixture Control - SET to FULL RICH (full forward) until stable
fuel flow is indicated (approximately 3 to 5 seconds), then set to
IDLE CUTOFF (full aft) position.
14. FUEL PUMP Switch - OFF
15. MAGNETOS Switch - START (release when engine starts)
16. Mixture Control - ADVANCE SMOOTHLY TO RICH (when
engine starts)
NOTE
If the engine is primed too much (flooded), place the
mixture control in the IDLE CUTOFF position, open the
throttle control 1/2 to full, and engage the starter motor
(START). When the engine starts, advance the mixture
control to the FULL RICH position and retard the throttle
control promptly.
(Continued Next Page)
4-12
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
STARTING ENGINE (With Battery) (Continued)
17. Oil Pressure - CHECK (verify that oil pressure increases into the
GREEN BAND range in 30 to 60 seconds)
18. AMPS (M BATT and BATT S) - CHECK (verify charge shown
(positive))
19. LOW VOLTS Annunciator - CHECK (verify annunciator is not
shown)
20. NAV Light Switch - ON as required
21. AVIONICS Switch (BUS 1 and BUS 2) - ON
STARTING ENGINE (With External Power)
1. Throttle Control - OPEN 1/4 INCH
2. Mixture Control - IDLE CUTOFF (pull full out)
3. STBY BATT Switch:
a. TEST - (hold for 20 seconds, verify green TEST lamp does
not go off)
b. ARM - (verify that PFD comes on)
4. Engine Indication System - CHECK PARAMETERS (verify no
red X's through ENGINE page indicators)
5. BUS E Volts - CHECK (verify 24 VOLTS minimum shown)
6. M BUS Volts - CHECK (verify 1.5 VOLTS or less shown)
7. BATT S Amps - CHECK (verify discharge shown (negative))
8. STBY BATT Annunciator - CHECK (verify annunciator is shown)
9. AVIONICS Switch (BUS 1 and BUS 2) - OFF
10. MASTER Switch (ALT and BAT) - OFF
11. Propeller Area - CLEAR (verify that all people and equipment
are at a safe distance from the propeller)
12. External Power - CONNECT (to ground power receptacle)
13. MASTER Switch (ALT and BAT) - ON
14. BEACON Light Switch - ON
15. M BUS VOLTS - CHECK (verify that approximately 28 VOLTS is
shown)
NOTE
If engine is warm, omit priming procedure steps 16 thru 18
below.
16. FUEL PUMP Switch - ON
(Continued Next Page)
172RPHBUS-00
U.S.
4-13
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
STARTING ENGINE (With External Power) (Continued)
17. Mixture Control - SET to FULL RICH (full forward) until stable
fuel flow is indicated (approximately 3 to 5 seconds), then set to
IDLE CUTOFF (full aft) position.
18. FUEL PUMP Switch - OFF
19. MAGNETOS Switch - START (release when engine starts)
20. Mixture Control - ADVANCE SMOOTHLY TO RICH (when
engine starts)
NOTE
If the engine is primed too much (flooded), place the
mixture control in the IDLE CUTOFF position, open the
throttle control 1/2 to full, and engage the starter motor
(START). When the engine starts, advance the mixture
control to the FULL RICH position and retard the throttle
control promptly.
21. Oil Pressure - CHECK (verify oil pressure increases into the
GREEN BAND range in 30 to 60 seconds)
22. Power - REDUCE TO IDLE
23. External Power - DISCONNECT FROM GROUND POWER
(latch external power receptacle door)
24. Power - INCREASE (to approximately 1500 RPM for several
minutes to charge battery)
25. AMPS (M BATT and BATT S) - CHECK (verify charge shown
(positive))
26. LOW VOLTS Annunciator - CHECK (verify annunciator is not
shown)
27. Internal Power - CHECK
a. MASTER Switch (ALT) - OFF
b. TAXI and LAND Light Switches - ON
c. Throttle Control - REDUCE TO IDLE
d. MASTER Switch (ALT and BAT) - ON
e. Throttle Control - INCREASE (to approximately 1500 RPM)
f. M BATT Ammeter - CHECK (verify battery charging, amps
positive)
g. LOW VOLTS Annunciator - CHECK (verify annunciator is
not shown)
(Continued Next Page)
4-14
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
STARTING ENGINE (With External Power) (Continued)
WARNING
IF M BATT AMMETER DOES NOT SHOW POSITIVE
CHARGE (+ AMPS), OR LOW VOLTS ANNUNCIATOR
DOES NOT GO OFF, REMOVE THE BATTERY FROM
THE AIRPLANE AND SERVICE OR REPLACE THE
BATTERY BEFORE FLIGHT.
28. NAV Light Switch - ON (as required)
29. AVIONICS Switch (BUS 1 and BUS 2) - ON
BEFORE TAKEOFF
1.
2.
3.
4.
5.
6.
7.
Parking Brake - SET
Pilot and Passenger Seat Backs - MOST UPRIGHT POSITION
Seats and Seat Belts - CHECK SECURE
Cabin Doors - CLOSED and LOCKED
Flight Controls - FREE and CORRECT
Flight Instruments (PFD) - CHECK (no red X's)
Altimeters:
a. PFD (BARO) - SET
b. Standby Altimeter - SET
8. ALT SEL - SET
9. Standby Flight Instruments - CHECK
10. Fuel Quantity - CHECK (verify level is correct)
NOTE
Flight is not recommended when both fuel quantity
indicators are in the yellow band range.
11. Mixture Control - RICH
12. FUEL SELECTOR Valve - SET BOTH
13. Autopilot - ENGAGE (if installed)
(push AP button on either PFD or MFD bezel)
14. Flight Controls - CHECK (verify autopilot can be overpowered in
both pitch and roll axes)
(Continued Next Page)
172RPHBUS-00
U.S.
4-15
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
BEFORE TAKEOFF (Continued)
15. A/P TRIM DISC Button - PRESS (if installed)
(verify autopilot disengages and aural alert is heard)
16. Flight Director - OFF (if installed)
(push FD button on either PFD or MFD bezel)
17. Elevator Trim Control - SET FOR TAKEOFF
18. Throttle Control - 1800 RPM
a. MAGNETOS Switch - CHECK (RPM drop should not
exceed 150 RPM on either magneto or 50 RPM differential
between magnetos)
b. VAC Indicator - CHECK
c. Engine Indicators - CHECK
d. Ammeters and Voltmeters - CHECK
19. Annunciators - CHECK (verify no annunciators are shown)
20. Throttle Control - CHECK IDLE
21. Throttle Control - 1000 RPM or LESS
22. Throttle Control Friction Lock - ADJUST
23. COM Frequency(s) - SET
24. NAV Frequency(s) - SET
25. FMS/GPS Flight Plan - AS DESIRED
NOTE
Check GPS availability on AUX-GPS STATUS page. No
annunciation is provided for loss of GPS2.
26. XPDR - SET
(Continued Next Page)
4-16
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
BEFORE TAKEOFF (Continued)
27. CDI Softkey - SELECT NAV SOURCE
CAUTION
T H E G 1 0 0 0 H S I S H O W S A C O U R S E D E VI ATI O N
INDICATOR FOR THE SELECTED GPS, NAV 1 OR NAV 2
NAVIGATION SOURCE. THE G1000 HSI DOES NOT
P R O V I D E A WA R N I N G F L A G W H E N A VA L I D
NAVIGATION SIGNAL IS NOT BEING SUPPLIED TO THE
INDICATOR. WHEN A VALID NAVIGATION SIGNAL IS
NOT BEING SUPPLIED, THE COURSE DEVIATION BAR
(D-BAR) PART OF THE INDICATOR IS NOT SHOWN ON
THE HSI COMPASS CARD. THE MISSING D-BAR IS
CONSIDERED TO BE THE WARNING FLAG.
WARNING
WHEN THE AUTOPILOT IS ENGAGED IN NAV, APR OR
BC OPERATING MODES, IF THE HSI NAVIGATION
SOURCE IS CHANGED MANUALLY, USING THE CDI
SOFTKEY, THE CHANGE WILL INTERRUPT THE
NAVIGATION SIGNAL TO THE AUTOPILOT AND WILL
CAUSE THE AUTOPILOT TO REVERT TO ROL MODE
OPERATION. NO AURAL ALERT WILL BE PROVIDED.
IN ROL MODE, THE AUTOPILOT WILL ONLY KEEP THE
WINGS LEVEL AND WILL NOT CORRECT THE
AIRPLANE HEADING OR COURSE. SET THE HDG BUG
TO THE CORRECT HEADING AND SELECT THE
CORRECT NAVIGATION SOURCE ON THE HSI, USING
THE CDI SOFTKEY, BEFORE ENGAGING THE
AUTOPILOT IN ANY OTHER OPERATING MODE.
28.
29.
30.
31.
32.
CABIN PWR 12V Switch - OFF
Wing Flaps - UP - 10° (10° preferred)
Cabin Windows - CLOSED and LOCKED
STROBE Light Switch - ON
Brakes - RELEASE
172RPHBUS-00
U.S.
4-17
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
TAKEOFF
NORMAL TAKEOFF
1. Wing Flaps - UP - 10° (10° preferred)
2. Throttle Control - FULL (push full in)
3. Mixture Control - RICH (above 3000 feet pressure altitude, lean
for maximum RPM)
4. Elevator Control - LIFT NOSEWHEEL AT 55 KIAS
5. Climb Airspeed - 70 - 80 KIAS
6. Wing Flaps - RETRACT (at safe altitude)
SHORT FIELD TAKEOFF
1.
2.
3.
4.
5.
6.
7.
8.
4-18
Wing Flaps - 10°
Brakes - APPLY
Throttle Control - FULL (push full in)
Mixture Control - RICH (above 3000 feet pressure altitude, lean
for maximum RPM)
Brakes - RELEASE
Elevator Control - SLIGHTLY TAIL LOW
Climb Airspeed - 57 KIAS (until all obstacles are cleared)
Wing Flaps - RETRACT SLOWLY (when airspeed is more than
60 KIAS)
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
ENROUTE CLIMB
1. Airspeed - 70 - 85 KIAS
2. Throttle Control - FULL (push full in)
3. Mixture Control - RICH (above 3000 feet pressure altitude, lean
for maximum RPM)
NOTE
For maximum performance climb speeds, refer to Section
5, Figure 5-6, Maximum Rate of Climb at 2450 Pounds.
CRUISE
1. Power - 2000 - 2400 RPM (no more than 80% power
recommended)
2. Elevator Trim Control - ADJUST
3. Mixture Control - LEAN (for desired performance or economy)
4. FMS/GPS - REVIEW and BRIEF (OBS/SUSP softkey operation
for holding pattern procedure (IFR))
172RPHBUS-00
U.S.
4-19
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
DESCENT
1. Power - AS DESIRED
2. Mixture - ADJUST (if necessary to make engine run smoothly)
3. Altimeters:
a. PFD (BARO) - SET
b. Standby Altimeter - SET
4. ALT SEL - SET
5. CDI Softkey - SELECT NAV SOURCE
6. FMS/GPS - REVIEW and BRIEF (OBS/SUSP softkey operation
for holding pattern procedure (IFR))
CAUTION
TH E G1000 H S I SH O WS A C O U R S E D E V I AT ION
INDICATOR FOR THE SELECTED GPS, NAV 1 OR NAV 2
NAVIGATION SOURCE. THE G1000 HSI DOES NOT
P R O V I D E A WA R N I N G F L A G W H E N A VA L I D
NAVIGATION SIGNAL IS NOT BEING SUPPLIED TO THE
INDICATOR. WHEN A VALID NAVIGATION SIGNAL IS
NOT BEING SUPPLIED, THE COURSE DEVIATION BAR
(D-BAR) PART OF THE INDICATOR IS NOT SHOWN ON
THE HSI COMPASS CARD. THE MISSING D-BAR IS
CONSIDERED TO BE THE WARNING FLAG.
WARNING
WHEN THE AUTOPILOT IS ENGAGED IN NAV, APR OR
BC OPERATING MODES, IF THE HSI NAVIGATION
SOURCE IS CHANGED MANUALLY, USING THE CDI
SOFTKEY, THE CHANGE WILL INTERRUPT THE
NAVIGATION SIGNAL TO THE AUTOPILOT AND WILL
CAUSE THE AUTOPILOT TO REVERT TO ROL MODE
OPERATION. NO AURAL ALERT WILL BE PROVIDED.
IN ROL MODE, THE AUTOPILOT WILL ONLY KEEP THE
WINGS LEVEL AND WILL NOT CORRECT THE
AIRPLANE HEADING OR COURSE. SET THE HDG BUG
TO THE CORRECT HEADING AND SELECT THE
CORRECT NAVIGATION SOURCE ON THE HSI, USING
THE CDI SOFTKEY, BEFORE ENGAGING THE
AUTOPILOT IN ANY OTHER OPERATING MODE.
7. FUEL SELECTOR Valve - BOTH
8. Wing Flaps - AS DESIRED (UP - 10° below 110 KIAS)
(10° - FULL below 85 KIAS)
4-20
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
BEFORE LANDING
1.
2.
3.
4.
5.
6.
7.
Pilot and Passenger Seat Backs - MOST UPRIGHT POSITION
Seats and Seat Belts - SECURED and LOCKED
FUEL SELECTOR Valve - BOTH
Mixture Control - RICH
LAND and TAXI Light Switches - ON
Autopilot - OFF (if installed)
CABIN PWR 12V Switch - OFF
LANDING
NORMAL LANDING
1. Airspeed - 65 - 75 KIAS (Flaps UP)
2. Wing Flaps - AS DESIRED (UP - 10° below 110 KIAS)
(10° - FULL below 85 KIAS)
3. Airspeed - 60 - 70 KIAS (Flaps FULL)
4. Elevator Trim Control - ADJUST
5. Touchdown - MAIN WHEELS FIRST
6. Landing Roll - LOWER NOSEWHEEL GENTLY
7. Braking - MINIMUM REQUIRED
SHORT FIELD LANDING
1.
2.
3.
4.
5.
6.
7.
8.
Airspeed - 65 - 75 KIAS (Flaps UP)
Wing Flaps - FULL
Airspeed - 62 KIAS (until flare)
Elevator Trim Control - ADJUST
Power - REDUCE TO IDLE (as obstacle is cleared)
Touchdown - MAIN WHEELS FIRST
Brakes - APPLY HEAVILY
Wing Flaps - UP
(Continued Next Page)
172RPHBUS-00
U.S.
4-21
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
LANDING (Continued)
BALKED LANDING
1.
2.
3.
4.
Throttle Control - FULL (push full in)
Wing Flaps - RETRACT to 20°
Climb Speed - 55 KIAS
Wing Flaps - 10° (as obstacle is cleared), then UP (after
reaching a safe altitude and 60 KIAS)
AFTER LANDING
1. Wing Flaps - UP
SECURING AIRPLANE
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
4-22
Parking Brake - SET
Throttle Control - IDLE (pull full out)
Electrical Equipment - OFF
AVIONICS Switch (BUS 1 and BUS 2) - OFF
Mixture Control - IDLE CUTOFF (pull full out)
MAGNETOS Switch - OFF
MASTER Switch (ALT and BAT) - OFF
STBY BATT Switch - OFF
Control Lock - INSTALL
FUEL SELECTOR Valve - LEFT or RIGHT (to prevent
crossfeeding between tanks)
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
AMPLIFIED NORMAL PROCEDURES
PREFLIGHT INSPECTION
The preflight inspection, described in Figure 4-1 and adjacent checklist,
is required prior to each flight. If the airplane has been in extended
storage, has had recent major maintenance, or has been operated from
rough runways, a more extensive exterior inspection is recommended.
Before every flight, check the condition of main and nose landing gear
tires. Keep tires inflated to the pressure specified in Section 8, Airplane
Handling, Service And Maintenance. Examine tire sidewalls for
patterns of shallow cracks called weather checks. These cracks are
evidence of tire deterioration caused by age, improper storage, or
prolonged exposure to weather. Check the tread of the tire for depth,
wear, and cuts. Replace the tire if fibers are visible.
After major maintenance has been performed, the flight and trim tab
controls should be double checked for free and correct movement and
security. The security of all inspection plates on the airplane should be
checked following periodic inspections. If the airplane has been waxed
or polished, check the external static pressure source hole for
stoppage.
If the airplane has been kept in a crowded hangar, it should be checked
for dents and scratches on wings, fuselage, and tail surfaces, damage
to navigation, strobe lights, and avionics antennas. Check for damage
to the nosewheel steering system, the result of exceeding nosewheel
turning limits while towing.
(Continued Next Page)
172RPHBUS-00
U.S.
4-23
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PREFLIGHT INSPECTION (Continued)
Outside storage for long periods may result in dust and dirt
accumulation on the induction air filter, obstructions in airspeed system
lines, water contaminants in fuel tanks, and insect/bird/rodent nests in
any opening. If any water is detected in the fuel system, the fuel tank
sump quick drain valves, fuel reservoir quick drain valve, and fuel
strainer quick drain valve should all be thoroughly drained again. The
wings should then be gently rocked and the tail lowered to the ground
to move any further contaminants to the sampling points. Repeated
samples should then be taken at all quick drain points until all
contamination has been removed. If, after repeated sampling, evidence
of contamination still exists, the fuel tanks should be completely drained
and the fuel system cleaned.
If the airplane has been stored outside in windy or gusty areas, or tied
down adjacent to taxiing airplanes, special attention should be paid to
control surface stops, hinges, and brackets to detect the presence of
potential wind damage.
If the airplane has been operated from muddy fields or in snow or slush,
check the main and nose gear wheel fairings for obstructions and
cleanliness. Operation from a gravel or cinder field will require extra
attention to propeller tips and abrasion on leading edges of the
horizontal tail. Stone damage to the propeller can seriously reduce the
fatigue life of the blades.
Airplanes that are operated from rough fields, especially at high
altitudes, are subjected to abnormal landing gear abuse. Frequently
check all components of the landing gear, shock strut, tires, and
brakes. If the shock strut is insufficiently extended, undue landing and
taxi loads will be subjected to the airplane structure.
To prevent loss of fuel in flight, make sure the fuel tank filler caps are
tightly sealed after any fuel system check or servicing. Fuel system
vents should also be inspected for obstructions, ice or water, especially
after exposure to cold, wet weather.
4-24
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
STARTING ENGINE
In cooler weather, the engine compartment temperature drops off
rapidly following engine shutdown and the injector nozzle lines remain
nearly full of fuel.
In warmer weather, engine compartment temperatures may increase
rapidly following engine shutdown, and fuel in the lines will vaporize
and escape into the intake manifold. Hot weather starting procedures
depend considerably on how soon the next engine start is attempted.
Within the first 20 to 30 minutes after shutdown, the fuel manifold is
adequately primed and the empty injector nozzle lines will fill before the
engine dies. However, after approximately 30 minutes, the vaporized
fuel in the manifold will have nearly dissipated and some slight priming
could be required to refill the nozzle lines and keep the engine running
after the initial start. Starting a hot engine is facilitated by advancing the
mixture control promptly to 1/3 open when the engine starts, and then
smoothly to full rich as power develops.
If the engine does not continue to run, set the FUEL PUMP switch to
the ON position temporarily and adjust the throttle and/or mixture as
necessary to keep the engine running. In the event of over priming or
flooding, set the FUEL PUMP switch to OFF, open the throttle from 1/2
to full open, and continue cranking with the mixture in the IDLE
CUTOFF position (pull full out). When the engine fires, smoothly
advance the mixture control to full rich and retard the throttle to desired
idle speed.
If the engine is under primed (most likely in cold weather with a cold
engine), it will not start at all, and additional priming will be necessary.
After starting, if the oil pressure gage does not begin to show pressure
within 30 seconds in warmer temperatures and approximately one
minute in very cold weather, stop the engine and find the cause before
continued operation. Lack of oil pressure can cause serious engine
damage.
NOTE
Additional details concerning cold weather starting and
op e r a t i o n m a y b e f o u nd u n d e r C O L D W E AT H E R
OPERATION paragraphs in this section.
(Continued Next Page)
172RPHBUS-00
U.S.
4-25
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
STARTING ENGINE (Continued)
RECOMMENDED STARTER DUTY CYCLE
Operate the starter motor for 10 seconds followed by a 20 second cool
down period. This cycle can be repeated two additional times, followed
by a ten minute cool down period before resuming cranking. After cool
down, operate the starter motor again, three cycles of 10 seconds
followed by 20 seconds of cool down. If the engine still does not start,
try to find the cause.
LEANING FOR GROUND OPERATIONS
For all ground operations, after starting the engine and when the
engine is running smoothly:
1. Set the throttle control to 1200 RPM.
2. Lean the mixture for maximum RPM.
3. Set the throttle control to an RPM appropriate for ground
operations (800 to 1000 RPM recommended).
NOTE
If ground operation will be required after the BEFORE
TAKEOFF checklist is completed, lean the mixture again
(as described above) until ready for the TAKEOFF
checklist.
4-26
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
TAXIING
When taxiing, it is important that speed and use of brakes be held to a
minimum and that all controls be utilized (refer to Figure 4-2, Taxiing
Diagram) to maintain directional control and balance.
Taxiing over loose gravel or cinders should be done at low engine
speed to avoid abrasion and stone damage to the propeller tips.
NOTE
The LOW VOLTS annunciator may come on when the
engine is operated at low RPM with a high load on the
electrical system. If this is the case, the LOW VOLTS
annunciator will go off when the engine is run at higher
RPM to provide greater alternator system output. Verify that
the M BATT AMPS indication shows positive (charging)
current at the higher RPM.
(Continued Next Page)
172RPHBUS-00
U.S.
4-27
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
TAXIING (Continued)
TAXIING DIAGRAM
NOTE
Strong quartering tail winds require caution. Avoid sudden
bursts of the throttle and sharp braking when the airplane is
in this attitude. Use the steerable nosewheel and rudder to
maintain direction.
Figure 4-2
4-28
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
BEFORE TAKEOFF
WARM UP
If the engine idles, with the throttle against the idle stop, (approximately
600 RPM) and accelerates smoothly, the engine is warm enough for
takeoff. Since the engine is closely cowled for efficient in-flight engine
cooling, the airplane should be pointed into the wind to avoid
overheating during prolonged engine operation on the ground. Long
periods of idling may cause fouled spark plugs.
MAGNETO CHECK
The magneto check must be made at 1800 RPM. Turn the
MAGNETOS switch from the BOTH position to the R position. Note the
new RPM, then turn the MAGNETOS switch back to the BOTH position
to clear the spark plugs. Turn the MAGNETOS switch to the L position,
note the new RPM, then turn the switch back to the BOTH position.
RPM decrease should not be more than 150 RPM on either magneto or
be greater than 50 RPM differential between magnetos. If there is a
doubt concerning operation of the ignition system, RPM checks at
higher engine speeds will usually confirm whether a deficiency exists.
No RPM drop may indicate a faulty ground to one magneto or magneto
timing set in advance of the angle specified.
ALTERNATOR CHECK
Make sure that both the alternator and alternator control unit are
operating properly before night or instrument flight, or flights where
electrical power is essential. Check the electrical system during the
MAGNETO check (1800 RPM) by setting all electrical equipment
required for the flight to the ON position. When the alternator and
alternator control unit are both operating properly, the ammeters will
show zero or positive current (amps), the voltmeters should show
between 27 to 29 volts, and no electrical system annunciations will
appear. Reduce the electrical load before reducing engine speed so the
battery will not discharge while the engine is at idle.
(Continued Next Page)
172RPHBUS-00
U.S.
4-29
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
BEFORE TAKEOFF (Continued)
ELEVATOR TRIM
The elevator trim tab is in the takeoff position when the trim pointer is
aligned with the index mark on the pedestal cover. Adjust the trim
wheel during flight as necessary to make control wheel forces more
neutral.
LANDING LIGHTS
It is recommended that only the taxi light be used to enhance the
visibility of the airplane in the traffic pattern or enroute. This will extend
the service life of the landing light.
TAKEOFF
POWER CHECK
It is important to check full throttle engine operation early in the takeoff
roll. Any sign of rough engine operation or sluggish engine acceleration
is good cause for discontinuing the takeoff. If this occurs, you are
justified in making a thorough full throttle static run-up before another
takeoff is attempted. The engine should run smoothly and turn
approximately 2065 - 2165 RPM with the mixture leaned to provide
maximum RPM.
Full throttle run-ups over loose gravel are especially harmful to
propeller tips. When takeoffs must be made over a gravel surface,
advance the throttle slowly. This allows the airplane to start rolling
before high RPM is developed, and the gravel will be blown behind the
propeller rather than pulled into it.
Prior to takeoff from fields above 3000 feet pressure altitude, the
mixture should be leaned to give maximum RPM at full throttle, with the
airplane not moving.
After full throttle is applied, adjust the throttle friction lock clockwise to
prevent the throttle from moving back from a maximum power position.
Similar friction lock adjustments should be made as required in other
flight conditions to hold the throttle setting.
(Continued Next Page)
4-30
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
TAKEOFF (Continued)
WING FLAP SETTINGS
Normal takeoffs use wing flaps UP - 10°. Using 10° wing flaps reduces
the ground roll and total distance over an obstacle by approximately 10
percent. Flap deflections greater than 10° are not approved for
takeoff. If 10° wing flaps are used for takeoff, the flaps should stay at
10° until all obstacles are cleared and a safe flap retraction speed of 60
KIAS is reached. For a short field, 10° wing flaps and an obstacle
clearance speed of 57 KIAS should be used.
Soft or rough field takeoffs are performed with 10° flaps by lifting the
airplane off the ground as soon as practical in a slightly tail low attitude.
If no obstacles are ahead, the airplane should be leveled off
immediately to accelerate to a higher climb speed. When departing a
soft field with an aft C.G. loading, the elevator trim control should be
adjusted towards the nose down direction to give comfortable control
wheel forces during the initial climb.
CROSSWIND TAKEOFF
Takeoffs under strong crosswind conditions normally are performed
with the minimum flap setting necessary for the field length, to minimize
the drift angle immediately after takeoff. With the ailerons partially
deflected into the wind, the airplane is accelerated to a speed slightly
higher than normal, then the elevator control is used to quickly, but
carefully, lift the airplane off the ground and to prevent possible settling
back to the runway while drifting. When clear of the ground, make a
coordinated turn into the wind to correct for drift.
172RPHBUS-00
U.S.
4-31
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ENROUTE CLIMB
Normal enroute climbs are performed with flaps up, at full throttle and
75 to 85 KIAS for the best combination of performance, visibility and
engine cooling. The mixture should be full rich during climb at altitudes
up to 3000 feet pressure altitude. Above 3000 feet pressure altitude,
the mixture can be leaned as needed for increased power or to provide
smoother engine operation.
If it is necessary to climb more rapidly to clear mountains or reach
favorable winds at higher altitudes, the best rate of climb speed should
be used with Maximum Continuous Power (MCP). This speed is 79
KIAS at sea level, decreasing to 71 KIAS at 10,000 feet.
If an obstruction dictates the use of a steep climb angle, the best angle
of climb speed should be used with flaps UP and MCP. This speed is 60
KIAS at sea level, increasing to 65 KIAS at 10,000 feet. This type of
climb should be of the minimum duration and engine temperatures
should be carefully monitored due to the low climb speed.
4-32
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
CRUISE
Normal cruise is performed between 60% and 80% power. The engine
RPM and corresponding fuel consumption for various altitudes can be
determined by using the data in Section 5.
NOTE
Cruise flight should use 80% power as much as possible
until the engine has operated for a total of 50 hours or oil
consumption has stabilized. Operation at this higher power
will ensure proper seating of the piston rings and is
applicable to new engines, and engines in service following
cylinder replacement or top overhaul of one or more
cylinders.
The Cruise Performance charts in Section 5 provide the pilot with flight
planning information for the Model 172R in still air with speed fairings
installed. Power, altitude, and winds determine the time and fuel
needed to complete any flight.
The Cruise Performance Table, Figure 4-3, shows the true airspeed
and nautical miles per gallon during cruise for various altitudes and
percent powers, and is based on standard conditions and zero wind.
This table should be used as a guide, along with the available winds
aloft information, to determine the most favorable altitude and power
setting for a given trip. The selection of cruise altitude on the basis of
the most favorable wind conditions and the use of low power settings
are significant factors that should be considered on every trip to reduce
fuel consumption.
In addition to power settings, proper leaning techniques also contribute
to greater range and are figured into cruise performance tables. To
achieve the recommended lean mixture fuel consumption figures
shown in Section 5, the mixture should be leaned using the Exhaust
Gas Temperature (EGT) indicator as noted.
(Continued Next Page)
172RPHBUS-00
U.S.
4-33
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CRUISE (Continued)
CRUISE PERFORMANCE TABLE
CONDITIONS:
Standard Conditions
ALTITUDE
Zero Wind
80% POWER
70% POWER
60% POWER
FEET
KTAS
NMPG
KTAS
NMPG
KTAS
NMPG
Sea Level
113
12.3
108
13.4
100
14.5
4000
117
12.8
111
13.9
103
14.9
8000
122
13.3
115
14.3
105
15.3
Figure 4-3
The Cruise Performance charts in Section 5 provide the pilot with
cruise performance at maximum gross weight. When normal cruise is
performed at reduced weights there is an increase in true airspeed.
During normal cruise at power settings between 60% and 80%, the true
airspeed will increase approximately 1 knot for every 150 pounds below
maximum gross weight. During normal cruise at power settings below
70%, the true airspeed will increase approximately 1 knot for every 125
pounds below maximum gross weight.
The fuel injection system employed on this engine is considered to be
non-icing. In the event that unusual conditions cause the intake air filter
to become clogged or iced over, an alternate intake air door opens
automatically for the most efficient use of either normal or alternate air,
depending on the amount of filter blockage. Due to the lower intake
pressure available through the alternate air door or a partially blocked
filter, engine RPM can decrease from a cruise power setting. This RPM
loss should be recovered by increasing the throttle setting to maintain
desired power.
(Continued Next Page)
4-34
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
CRUISE (Continued)
LEANING USING EXHAUST GAS TEMPERATURE (EGT)
The cruise performance data in this POH is based on the
recommended lean mixture setting determined from the maximum or
peak EGT at power settings of 80% MCP and lower. The 172R Nav III
provides EGT indications for all (4) engine cylinders. The ability to
monitor all cylinders is an aid in early identification and correction of
fuel injection problems.
NOTE
All engine cylinders do not receive identical fuel/air mixtures
(due to unequal intake pipe lengths, uneven intake air
temperatures, fuel injection nozzle tolerances etc.).
However, all cylinder EGTs should be within approximately
100°F of each other during normal operations. An EGT
difference greater than 100°F between cylinders indicates
that fuel injection system maintenance is necessary.
EGT is displayed on the EIS ENGINE and LEAN pages. The ENGINE
page has a horizontal scale with a temperature indicator (inverted
triangle) with a number representing the cylinder with the highest EGT.
The EIS LEAN page provides vertical bar graph displays showing EGT
for all cylinders. The cylinder with the highest EGT is shown in cyan
(light blue). The numerical value for the highest EGT is located below
the bar. The EGT and Cylinder Head Temperature (CHT) value for any
cylinder may be shown by using the CYL SLCT softkey to select the
desired cylinder. After a short period without CYL SLCT softkey activity,
automatic indication of the highest EGT and CHT will start again.
(Continued Next Page)
172RPHBUS-00
U.S.
4-35
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CRUISE (Continued)
LEANING USING EXHAUST GAS TEMPERATURE (EGT)
(Continued)
To aid in leaning the mixture, push the ENGINE, LEAN and ASSIST
softkeys, ΔPEAK °F will display below the EGT °F numerical value.
Lean the mixture by slowly turning the mixture control knob in the
counterclockwise direction while monitoring EGTs. As EGTs increase,
continue to lean the mixture until the hottest (cyan) cylinder reaches
peak EGT. This is identified by the EGT bar graph for that cylinder
changing to cyan with a hollow bar at the top. Note the ΔPEAK °F and
FFLOW GPH values for the first peaked cylinder. Peak EGT is
represented by ΔPEAK 0°F, if ΔPEAK °F value is negative (-) the
mixture can be on the lean side of peak. Enrichen the mixture by slowly
turning the mixture control clockwise and monitor both fuel flow and
EGTs until the leanest cylinder returns to peak EGT (ΔPEAK 0°F) or
desired setting based on the Exhaust Gas Temperature (EGT) Table,
Figure 4-4.
ΔPEAK °F values rich of peak will also be a negative (-) value (-50°F).
The lean assist system calculation is defined such that the peak EGT is
the highest value and any lesser value is represented with a negative () value, whether on the lean or rich side of the peak.
NOTE
The 172R engine manufacturer, Textron Lycoming, has not
approved operation of the engine at fuel flow rates (mixture
settings) less than necessary to reach peak EGT in the
leanest cylinder (the first cylinder to reach peak EGT). Use
FULL RICH mixture when operating the engine above 80%
power.
(Continued Next Page)
4-36
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
CRUISE (Continued)
LEANING USING EXHAUST GAS TEMPERATURE (EGT)
(Continued)
EXHAUST GAS TEMPERATURE (EGT)
MIXTURE DESCRIPTION
EXHAUST GAS
TEMPERATURE (EGT)
RECOMMENDED LEAN
(Pilot’s Operating Handbook)
50°F Rich of Peak EGT
BEST ECONOMY
Peak EGT
Figure 4-4
Operation at peak EGT provides the best fuel economy. This results in
approximately 4% greater range than shown in this POH accompanied
by approximately a 3 knot decrease in speed.
Under some conditions, engine roughness may occur while operating
at peak EGT. In this case, operate at the recommended lean mixture.
NOTE
•
Any change in altitude or power setting will require a
change in the recommended lean mixture setting and a
recheck of the EGT setting.
•
The EGT indicators take several seconds, after a mixture
adjustment, to start to show EGT changes. Finding peak
EGT and adjusting the mixture to the applicable setting
should take approximately one minute when the
adjust ments are made carefully and ac curately.
Adjusting the mixture quickly is not recommended.
(Continued Next Page)
172RPHBUS-00
U.S.
4-37
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CRUISE (Continued)
FUEL SAVINGS PROCEDURES FOR FLIGHT TRAINING
OPERATIONS
For best fuel economy during flight training operations, the following
procedures are recommended.
1. After engine start and for all ground operations, set the throttle to
1200 RPM and lean the mixture for maximum RPM. After
leaning, set the throttle to the appropriate RPM for ground
operations. Leave the mixture at this setting until beginning the
BEFORE TAKEOFF checklist. After the BEFORE TAKEOFF
checklist is complete, lean the mixture again as described above
until ready to perform the TAKEOFF checklist.
2. Lean the mixture for maximum RPM during full throttle climbs
above 3000 feet. The mixture may remain leaned (maximum
RPM at full throttle) for practicing maneuvers such as stalls and
slow flight.
3. Lean the mixture for maximum RPM during all operations at any
altitude, including those below 3000 feet, when using 80% or
less power.
NOTE
•
When cruising or maneuvering at 80% power or less, the
mixture may be further leaned until the EGT indicator
peaks and is then enrichened 50°F. This is especially
applicable to cross-country training flights, but should be
practiced during transition flight to and from the practice
area as well.
•
Using the above recommended procedures can provide
fuel savings in excess of 5% when compared to typical
training operations at full rich mixture. In addition, the
above procedures will minimize spark plug fouling since
the reduction in fuel consumption results in a
proportional reduction in tetraethyl lead passing through
the engine.
(Continued Next Page)
4-38
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
CRUISE (Continued)
FUEL VAPOR PROCEDURES
The engine fuel system can cause fuel vapor formation on the ground
during warm weather. This will generally occur when the outside
ambient air temperature is above 80°F. Vapor formation may increase
when the engine fuel flows are lower at idle and taxi engine speeds.
The following procedures are recommended when engine idle speed
and fuel flow fluctuations show that fuel vapor may be present:
1. With the mixture full rich, set the throttle at 1800 RPM to 2000
RPM. Maintain this power setting for 1 to 2 minutes or until
smooth engine operation returns.
2. Retard the throttle to idle to verify normal engine operation.
3. Advance the throttle to 1200 RPM and lean the mixture as
described under FUEL SAVINGS PROCEDURES FOR FLIGHT
TRAINING OPERATIONS.
4. In addition to the above procedures, the auxiliary fuel pump may
be turned ON with the mixture adjusted as required to aid vapor
suppression during ground operations. The auxiliary fuel pump
should be turned OFF prior to takeoff.
5. Just prior to TAKEOFF, apply full throttle for approximately 10
seconds to verify smooth engine operation for takeoff.
NOTE
When the engine is operated above 1800 RPM, the
result i ng incre ase d fuel fl ow result s i n l ow er fu el
temperatures throughout the engine fuel system. This
increased flow purges the fuel vapor and the cooler fuel
minimizes vapor formation.
(Continued Next Page)
172RPHBUS-00
U.S.
4-39
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CRUISE (Continued)
FUEL VAPOR PROCEDURES (Continued)
In addition to the previous procedures, the sections below should be
reviewed, and where applicable, adhered to:
Section 3 -Take note of the excessive fuel vapor procedures in both
the checklist and the amplified procedures sections.
Section 4 -Take note of the hot weather operational notes and
procedures in both the checklist and the amplified
procedures sections.
STALLS
The stall characteristics are conventional and aural warning is provided
by a stall warning horn which sounds between 5 and 10 knots above
the stall in all configurations.
Power off stall speeds at maximum weight for both forward and aft C.G.
positions are presented in Section 5.
SPINS
Intentional spins are approved when the airplane is operated in the
utility category. Spins with baggage loadings or occupied rear seat(s)
are not approved.
However, before attempting to perform spins several items should be
carefully considered to assure a safe flight. No spins should be
attempted without first having received dual instruction both in spin
entries and spin recoveries from a qualified instructor who is familiar
with the spin characteristics of the Cessna 172R NAV III airplane.
The cabin should be clean and all loose equipment (including the
microphone and rear seat belts) should be stowed or secured. For a
solo flight in which spins will be conducted, the front passenger's seat
belt and shoulder harness should also be secured. Care should be
taken to ensure that the pilot can easily reach the flight controls and
produce maximum control travels.
(Continued Next Page)
4-40
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
SPINS (Continued)
It is recommended that entries be accomplished at high enough altitude
that recoveries are completed 4000 feet or more Above Ground Level
(AGL). At least 1000 feet of altitude loss should be allowed for a 1-turn
spin and recovery, while a 6-turn spin and recovery may require
somewhat more than twice that amount. For example, the
recommended entry altitude for a 6-turn spin would be 6000 feet AGL.
In any case, entries should be planned so that recoveries are
completed well above the minimum 1500 feet AGL required by 14 CFR
91.303. Another reason for using high altitudes for practicing spins is
that a greater field of view is provided which will assist in maintaining
pilot orientation.
The normal entry is made from a power off stall. As the stall is
approached, the elevator control should be smoothly pulled to the full
aft position. Just prior to reaching the stall "break", rudder control in the
desired direction of the spin rotation should be applied so that full
rudder deflection is reached almost simultaneously with reaching full aft
elevator. A slightly greater rate of deceleration than for normal stall
entries, application of ailerons in the direction of the desired spin, and
the use of power at the entry will assure more consistent and positive
entries to the spin. As the airplane begins to spin, reduce the power to
idle and return the ailerons to neutral. Both elevator and rudder controls
should be held full with the spin until the spin recovery is initiated. An
inadvertent relaxation of either of these controls could result in the
development of a nose down spiral.
For the purpose of training in spins and spin recoveries, a 1 or 2 turn
spin is adequate and should be used. Up to 2 turns, the spin will
progress to a fairly rapid rate of rotation and a steep attitude.
Application of recovery controls will produce prompt recoveries (within
1/4 turn). During extended spins of two to three turns or more, the spin
will tend to change into a spiral, particularly to the right. This will be
accompanied by an increase in airspeed and gravity loads on the
airplane. If this occurs, recovery should be accomplished promptly but
smoothly by leveling the wings and recovering from the resulting dive.
(Continued Next Page)
172RPHBUS-00
U.S.
4-41
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SPINS (Continued)
Regardless of how many turns the spin is held or how it is entered, the
following recovery technique should be used:
1. VERIFY THAT THROTTLE IS IN IDLE POSITION AND
AILERONS ARE NEUTRAL.
2. APPLY AND HOLD FULL RUDDER OPPOSITE TO THE
DIRECTION OF ROTATION.
3. JUST AFTER THE RUDDER REACHES THE STOP, MOVE
THE CONTROL WHEEL BRISKLY FORWARD FAR ENOUGH
TO BREAK THE STALL.
4. HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS.
5. AS ROTATION STOPS, NEUTRALIZE RUDDER, AND MAKE A
SMOOTH RECOVERY FROM THE RESULTING DIVE.
NOTE
If disorientation makes the direction of rotation difficult to
determine, see the turn vector near the index at the top of
the Horizontal Situation Indicator (HSI).
Variations in basic airplane rigging or in weight and balance due to
installed equipment or right seat occupancy can cause differences in
behavior, particularly in extended spins. These differences are normal
and will result in variations in the spin characteristics and in the
spiraling tendencies for spins of more than 2 turns. However, the
recovery technique should always be used and will result in the most
expeditious recovery from any spin.
Intentional spins with flaps extended are prohibited, since the high
airspeeds which may occur during recovery can be more than the flap
airspeed limitation and can damage the flap and wing structures.
4-42
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
LANDING
NORMAL LANDING
Normal landing approaches can be made with power on or power off
with any flap setting within the flap airspeed limits. Surface winds and
air turbulence are usually the primary factors in determining the most
comfortable approach speeds. Steep slips with flap settings greater
than 20° can cause a slight tendency for the elevator to oscillate under
certain combinations of airspeed, sideslip angle, and center of gravity
loadings.
Landing at slower speeds will result in shorter landing distances and
minimum wear to tires and brakes. Power must be at idle as the main
wheels touch the ground. The main wheels must touch the ground
before the nosewheel. The nosewheel must be lowered to the runway
carefully after the speed has diminished to avoid unnecessary nose
gear loads. This procedure is very important for rough or soft field
landings.
SHORT FIELD LANDING
For a short field landing in smooth air conditions, approach at 62 KIAS
with FULL flaps using enough power to control the glide path. Slightly
higher approach speeds should be used in turbulent air conditions.
After all approach obstacles are cleared, smoothly reduce power and
hold the approach speed by lowering the nose of the airplane. The
main wheels must touch the ground before the nosewheel with power
at idle. Immediately after the main wheels touch the ground, carefully
lower the nosewheel and apply heavy braking as required. For
maximum brake performance, retract the flaps, hold the control wheel
full back, and apply maximum brake pressure without skidding the tires.
(Continued Next Page)
172RPHBUS-00
U.S.
4-43
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
LANDING (Continued)
CROSSWIND LANDING
When landing in a strong crosswind, use the minimum flap setting
required for the field length. If flap settings greater than 20° are used in
sideslips with full rudder deflection, some elevator oscillation may be
felt at normal approach speeds. However, this does not affect control of
the airplane. Although the crab or combination method of drift
correction may be used, the wing low method gives the best control.
After touchdown, hold a straight course with the steerable nosewheel,
with aileron deflection as applicable, and occasional braking if
necessary.
The maximum allowable crosswind velocity is dependent upon pilot
capability as well as airplane limitations. Operation in direct crosswinds
of 15 knots has been demonstrated (not an operating limitation).
BALKED LANDING
In a balked landing (go-around) climb, reduce the flap setting to 20°
immediately after full power is applied and climb at 55 KIAS. If
obstacles must be cleared during the go-around climb, reduce the wing
flap setting to 10° and maintain a safe airspeed until the obstacles are
cleared. Above 3000 feet pressure altitude, lean the mixture to obtain
maximum RPM. After clearing any obstacles, carefully retract the flaps
and allow the airplane to accelerate to normal climb airspeed.
4-44
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
COLD WEATHER OPERATIONS
Special consideration should be given to the operation of the airplane
fuel system during the winter season or prior to any flight in cold
temperatures. Proper preflight draining of the fuel system is especially
important and will eliminate any free water accumulation. The use of
additives such as isopropyl alcohol or Diethylene Glycol Monomethyl
Ether (DIEGME) may also be desirable. Refer to Section 8 for
information on the proper use of additives.
Cold weather often causes conditions that require special care during
airplane operations. Even small accumulations of frost, ice, or snow
must be removed, particularly from wing, tail and all control
surfaces to assure satisfactory flight performance and handling.
Also, control surfaces must be free of any internal accumulations of ice
or snow.
If snow or slush covers the takeoff surface, allowance must be made for
takeoff distances which will be increasingly extended as the snow or
slush depth increases. The depth and consistency of this cover can, in
fact, prevent takeoff in many instances.
(Continued Next Page)
172RPHBUS-00
U.S.
4-45
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
COLD WEATHER OPERATION (Continued)
STARTING
When air temperatures are below 20°F (-6°C), use an external
preheater and an external power source whenever possible to obtain
positive starting and to reduce wear and abuse to the engine and
electrical system. Preheat will thaw the oil trapped in the oil cooler,
which probably will be congealed prior to starting in extremely cold
temperatures.
WARNING
WHEN TURNING THE PROPELLER BY HAND, TREAT IT
AS IF THE MAGNETOS SWITCH IS IN THE ON
POSITION. A LOOSE OR BROKEN GROUND WIRE ON
EITHER MAGNETO COULD ENERGIZE THE ENGINE.
Prior to starting on cold mornings, it is advisable to turn the propeller
manually through several engine compression cycles by hand to loosen
the oil, so the engine cranks (motors) more easily and uses less battery
power. When the propeller is turned manually, turn it in the opposite
direction to normal engine rotation for greater safety. Opposite rotation
disengages the magneto impulse couplings and prevents possible
unwanted ignition.
When using an external power source, the MASTER switch ALT and
BAT sections must be in the OFF position before connecting the
external power source to the airplane receptacle. Refer to Section 7,
External Power Receptacle, for external power source operations.
(Continued Next Page)
4-46
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 4
NORMAL PROCEDURES
COLD WEATHER OPERATION (Continued)
STARTING (Continued)
Cold weather starting procedures are the same as the normal starting
procedures. However, to conserve battery power the beacon light can
be left off until the engine is started. Use caution to prevent inadvertent
forward movement of the airplane during starting when parked on snow
or ice.
During cold weather starting, when performing the Standby Battery
energy level test, the test lamp may not illuminate and the BUS E volts
may be less than 24 volts before turning on the MASTER (ALT and
BAT) switch. After engine start, verify the S BATT ammeter shows a
charge (positive) at 1000 RPM or greater. Prior to takeoff verify the S
BATT ammeter shows a charge less than 0.4 amps.
NOTE
If the engine does not start during the first few attempts, or
if engine firing diminishes in strength, the spark plugs may
be frosted over. Preheat must be used before another start
is attempted.
During cold weather operations, the oil temperature indicator may not
be in the green band prior to takeoff if outside air temperatures are very
cold. After a suitable warm up period (2 to 5 minutes at 1000 RPM),
accelerate the engine several times to higher engine RPMs. If the
engine accelerates smoothly and the oil pressure remains normal and
steady, the airplane is ready for takeoff.
WINTERIZATION KIT
An optional winterization kit is available and may be utilized when cold
weather operations are conducted. Refer to Section 9, Supplement 4
for installation and operational details.
172RPHBUS-00
U.S.
4-47
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
HOT WEATHER OPERATIONS
Refer to the general warm temperature starting information under
Starting Engine in this section. Avoid prolonged engine operation on the
ground.
NOISE CHARACTERISTICS
The certified takeoff noise level for the Model 172R at 2450 pounds
maximum weight is 73.3 dB(A) per 14 CFR 36 Appendix G (through
Amendment 36-21) and 76.3 dB(A) per ICAO Annex 16 Chapter 10
(through Amendment 4). No determination has been made that the
noise levels of this airplane are, or should be, acceptable or
unacceptable for operation at, into, or out of, any airport.
The following procedures are suggested to minimize the effect of
airplane noise on the public:
1. Pilots operating airplanes under VFR over outdoor assemblies
of persons, recreational and park areas, and other noise
sensitive areas should make every effort to fly not less than
2000 feet AGL, weather permitting, even though flight at a lower
level may be consistent with the provisions of government
regulations.
2. During departure from or approach to an airport, climb after
takeoff and descent for landing should be made so as to avoid
prolonged flight at low altitude near noise sensitive areas.
NOTE
The above recommended procedures do not apply where
they would conflict with Air Traffic Control clearances or
instructions, or where, in the pilot's judgment, an altitude of
less than 2000 feet AGL is necessary to adequately
exercise the duty to see and avoid other airplanes.
4-48
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
PERFORMANCE
TABLE OF CONTENTS
Page
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-3
Use of Performance Charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-3
Sample Problem . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-4
Takeoff. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-5
Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-6
Fuel Required . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-7
Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9
Demonstrated Operating Temperature . . . . . . . . . . . . . . . . . . . . . . . 5-9
Airspeed Calibration - Normal Static Source . . . . . . . . . . . . . . . . . . 5-10
Airspeed Calibration - Alternate Static Source. . . . . . . . . . . . . . . . . 5-11
Temperature Conversion Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-12
Stall Speeds At 2450 Pounds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-13
Crosswind Component . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-14
Short Field Takeoff Distance At 2450 Pounds . . . . . . . . . . . . . . . . . 5-15
Maximum Rate Of Climb At 2450 Pounds . . . . . . . . . . . . . . . . . . . . 5-16
Time, Fuel And Distance To Climb At 2450 Pounds . . . . . . . . . . . . 5-17
Cruise Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-18
Range Profile . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-20
Endurance Profile . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-21
Short Field Landing Distance At 2450 Pounds . . . . . . . . . . . . . . . . 5-22
172RPHBUS-00
U.S.
5-1/5-2
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
INTRODUCTION
Performance data charts on the following pages are presented so that
you may know what to expect from the airplane under various
conditions and to facilitate the planning of flights in detail with
reasonable accuracy. The data in the charts has been computed from
actual flight tests with the airplane and engine in good condition and
using average piloting techniques.
It should be noted that performance information presented in the range
and endurance profile charts allows for 45 minutes reserve fuel at the
specified power setting. Fuel flow data for cruise is based on the
recommended lean mixture setting at all altitudes. Some indeterminate
variables such as mixture leaning technique, fuel metering
characteristics, engine and propeller condition, and air turbulence may
account for variations of 10% or more in range and endurance.
Therefore, it is important to utilize all available information to estimate
the fuel required for the particular flight and to flight plan in a
conservative manner.
USE OF PERFORMANCE CHARTS
Performance data is presented in tabular or graphical form to illustrate
the effect of different variables. Sufficiently detailed information is
provided in the tables so that conservative values can be selected and
used to determine the particular performance figure with reasonable
accuracy.
172RPHBUS-00
U.S.
5-3
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SAMPLE PROBLEM
The following sample flight problem utilizes information from the
various charts to determine the predicted performance data for a typical
flight. Assume the following information has already been determined:
AIRPLANE CONFIGURATION:
Takeoff weight
Usable fuel
2450 Pounds
53.0 Gallons
TAKEOFF CONDITIONS:
Field pressure altitude
Temperature
Wind component along runway
Field length
1500 Feet
28°C (16°C Above Standard)
12 Knot Head Wind
3500 Feet
CRUISE CONDITIONS:
Total distance
Pressure altitude
Temperature
Expected wind enroute
360 Nautical Miles
5500 Feet
20°C (16°C Above Standard)
10 Knot Head Wind
LANDING CONDITIONS:
Field pressure altitude
Temperature
Field length
2000 Feet
25°C
3000 Feet
(Continued Next Page)
5-4
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
SAMPLE PROBLEM (Continued)
TAKEOFF
The takeoff distance chart, Figure 5-5, should be consulted, keeping in
mind that distances shown are based on the short field technique.
Conservative distances can be established by reading the chart at the
next higher value of weight, altitude and temperature. For example, in
this particular sample problem, the takeoff distance information
presented for a weight of 2450 pounds, pressure altitude of 2000 feet
and a temperature of 30°C should be used and results in the following:
Ground roll
Total distance to clear a 50-foot obstacle
1275 Feet
2290 Feet
These distances are well within the available takeoff field length.
However, a correction for the effect of wind may be made based on
information presented in the note section of the takeoff chart. The
correction for a 12 knot head wind is:
12 Knots
X 10% = 13% Decrease
9 Knots
This results in the following distances, corrected for wind:
Ground roll, zero wind
1275 Feet
Decrease in ground roll (1275 feet X 13%)
-166 Feet
Corrected ground roll
1109 Feet
Total distance to clear a 50-foot obstacle, zero wind 2290 Feet
Decrease in total distance (2290 feet X 13%)
-298 Feet
Corrected total distance to clear 50-foot obstacle
1992 Feet
(Continued Next Page)
172RPHBUS-00
U.S.
5-5
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SAMPLE PROBLEM (Continued)
CRUISE
The cruising altitude should be selected based on a consideration of
trip length, winds aloft and the airplane's performance. A typical
cruising altitude and the expected wind enroute have been given for
this sample problem. However, the power setting selection for cruise
must be determined based on several considerations. These include
the cruise performance characteristics presented in Figure 5-8, the
range profile chart presented in Figure 5-9, and the endurance profile
chart presented in Figure 5-10.
The relationship between power and range is illustrated by the range
profile chart. Considerable fuel savings and longer range result when
lower power settings are used. For this sample problem, a cruise power
of approximately 65% will be used.
The cruise performance chart, Figure 5-8, is entered at 6000 feet
pressure altitude and 20°C above standard temperature. These values
most nearly correspond to the planned altitude and expected
temperature conditions. The engine speed chosen is 2200 RPM, which
results in the following:
Power
True airspeed
Cruise fuel flow
64%
109 Knots
7.3 GPH
(Continued Next Page)
5-6
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
SAMPLE PROBLEM (Continued)
FUEL REQUIRED
The total fuel requirement for the flight may be estimated using the
performance information in Figure 5-7 and Figure 5-8. For this sample
problem, the time, fuel and distance to climb may be determined from
Figure 5-7 for normal climb. The difference between the values shown
in the table for 2000 feet and 6000 feet results in the following:
Time:
Fuel:
Distance:
7 Minutes
1.4 Gallons
10 Nautical Miles
These values are for a standard temperature and are sufficiently
accurate for most flight planning purposes. However, a further
correction for the effect of temperature may be made as noted on the
climb chart. The approximate effect of a nonstandard temperature is to
increase the time, fuel and distance by 10% for each 10°C above
standard temperature, due to the lower rate of climb. In this case,
assuming a temperature 16°C above standard the correction would be:
16°C
10°C
X 10% = 16% Increase
With this factor included, the fuel estimate would be calculated as
follows:
Fuel to climb, standard temperature
1.4 Gallons
Increase due to non-standard temperature (1.4 X 16%) 0.2 Gallons
Corrected fuel to climb
1.6 Gallons
Using a similar procedure for the distance to climb results in 12 nautical
miles.
The resultant cruise distance is:
Total distance
Climb distance
Cruise distance
360 Nautical Miles
-12 Nautical Miles
348 Nautical Miles
(Continued Next Page)
172RPHBUS-00
U.S.
5-7
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SAMPLE PROBLEM (Continued)
FUEL REQUIRED (Continued)
With an expected 10 knot head wind, the ground speed for cruise is
predicted to be:
109 Knots
-10 Knots
99 Knots
Therefore, the time required for the cruise portion of the trip is:
348 Nautical Miles = 3.5 Hours
99 Knots
The fuel required for cruise is:
3.5 hours X 7.3 gallons/hour = 25.6 Gallons
A 45-minute reserve requires:
45 X 7.3 gallons/hour = 5.5 Gallons
60
The total estimated fuel required is as follows:
Engine start, taxi, and takeoff
1.1 Gallons
Climb
1.6 Gallons
Cruise
25.6 Gallons
Reserve
5.5 Gallons
Total fuel required
33.8 Gallons
Once the flight is underway, ground speed checks will provide a more
accurate basis for estimating the time enroute and the corresponding
fuel required to complete the trip with ample reserve.
(Continued Next Page)
5-8
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
SAMPLE PROBLEM (Continued)
LANDING
A procedure similar to takeoff should be used for estimating the landing
distance at the destination airport. Figure 5-11 presents landing
distance information for the short field technique. The distances
corresponding to 2000 feet and 30°C are as follows:
Ground roll
Total distance to clear a 50-foot obstacle
625 Feet
1410 Feet
A correction for the effect of wind may be made based on information
presented in the note section of the landing chart, using the same
procedure as outlined for takeoff.
DEMONSTRATED OPERATING TEMPERATURE
Satisfactory engine cooling has been demonstrated for this airplane
with an outside air temperature 23°C above standard. This is not to be
considered as an operating limitation. Reference should be made to
Section 2 for engine operating limitations.
172RPHBUS-00
U.S.
5-9
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AIRSPEED CALIBRATION
NORMAL STATIC SOURCE
CONDITIONS:
Power required for level flight or maximum power descent.
Flaps
UP
KIAS
50 60 70 80 90 100 110 120 130 140 150 160
KCAS
56 62 70 79 89 98 107 117 126 135 145 154
Flaps
10°
KIAS
40 50 60 70 80 90 100 110 ---
---
---
---
KCAS
49 55 62 70 79 89 98 108 ---
---
---
---
KIAS
40 50 60 70 80 85
---
---
---
---
---
---
KCAS
47 53 61 70 80 84
---
---
---
---
---
---
Flaps
FULL
Figure 5-1 (Sheet 1 of 2)
5-10
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
AIRSPEED CALIBRATION
ALTERNATE STATIC SOURCE
HEATER OFF, VENTS AND WINDOWS CLOSED
FLAPS UP
--- 50 60 70 80 90 100 110 120
NORMAL KIAS
ALTERNATE KIAS --- 51 61 71 82 91 101 111 121
FLAPS 10°
40 50 60 70 80 90 100 110 --NORMAL KIAS
ALTERNATE KIAS 40 51 61 71 81 90 99 108 --FLAPS FULL
40 50 60 70 80 85 --- --- --NORMAL KIAS
ALTERNATE KIAS 38 50 60 70 79 81 --- --- ---
130 140
131 141
-----
-----
-----
-----
HEATER ON, VENTS OPEN AND WINDOWS CLOSED
FLAPS UP
40 50 60 70 80 90 100 110 120 130
NORMAL KIAS
ALTERNATE KIAS 36 48 59 70 80 89 99 108 118 128
FLAPS 10°
40 50 60 70 80 90 100 110 --- --NORMAL KIAS
ALTERNATE KIAS 38 49 59 69 79 88 97 106 --- --FLAPS FULL
40 50 60 70 80 85 --- --- --- --NORMAL KIAS
ALTERNATE KIAS 34 47 57 67 77 81 --- --- --- ---
140
139
---------
WINDOWS OPEN
FLAPS UP
NORMAL KIAS
ALTERNATE KIAS
FLAPS 10°
NORMAL KIAS
ALTERNATE KIAS
FLAPS FULL
NORMAL KIAS
ALTERNATE KIAS
40 50 60 70 80 90 100 110 120 130 140
26 43 57 70 82 93 103 113 123 133 143
40 50 60 70 80 90 100 110 --25 43 57 69 80 91 101 111 ---
-----
-----
40 50 60 70 80 85
25 41 54 67 78 84
-----
-----
-----
-----
-----
Figure 5-1 (Sheet 2)
172RPHBUS-00
U.S.
5-11
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
TEMPERATURE CONVERSION CHART
Figure 5-2
5-12
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
STALL SPEED AT 2450 POUNDS
CONDITIONS:
Power IDLE
MOST REARWARD CENTER OF GRAVITY
ANGLE OF BANK
FLAP
SETTING
0°
30°
45°
60°
KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS
UP
44
51
48
55
53
61
63
73
10°
35
48
38
52
42
58
50
69
FULL
33
47
36
50
40
56
47
66
MOST FORWARD CENTER OF GRAVITY
ANGLE OF BANK
FLAP
SETTING
0°
30°
45°
60°
KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS
UP
44
52
48
56
53
62
63
74
10°
37
50
40
53
44
59
53
70
FULL
33
47
36
50
40
56
47
66
NOTE
•
Altitude loss during a stall recovery may be as much as
230 feet.
•
KIAS values are approximate.
Figure 5-3
172RPHBUS-00
U.S.
5-13
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CROSSWIND COMPONENT
NOTE
Maximum demonstrated crosswind velocity is 15 knots (not
a limitation).
Figure 5-4
5-14
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
SHORT FIELD TAKEOFF DISTANCE
AT 2450 POUNDS
CONDITIONS:
Flaps 10°
Full Throttle prior to brake release.
Paved, Level, Dry Runway
Zero Wind
0°C
Lift Off:
Speed at 50 Feet:
10°C
20°C
30°C
51 KIAS
57 KIAS
40°C
Total
Total
Feet
Feet
Gnd
Gnd
Gnd
To
To
Roll Clear Roll Clear Roll
Feet 50 Feet 50 Feet
Foot
Foot
Obst
Obst
Total
Feet
To
Clear
50
Foot
Obst
Sea Level
845
1510
1745 1055 1875 1135 2015
1000
925
1660 1000 1790 1075 1925
2000
1015 1830 1095 1970 1185
3000
1115 2020 1205 2185 1305 2360 1400 2540 1505 2730
4000
1230 2245 1330 2430 1435 2630 1545 2830 1655 3045
5000
1355 2500 1470 2715 1585 2945 1705 3175 1830 3430
6000
1500 2805 1625 3060 1750 3315 1880 3590 2020 3895
7000
1660 3170 1795 3470 1935 3770 2085 4105 2240 4485
8000
1840 3620 1995 3975 2150 4345 2315 4775
Pressure
Altitude
Feet
910
1625
980
Total
Total
Feet
Feet
Gnd
Gnd
To
To
Roll Clear Roll Clear
Feet 50 Feet 50
Foot
Foot
Obst
Obst
1160 2070 1245 2220
2125 1275 2290 1365 2455
---
---
NOTE
•
•
•
•
•
Short field technique as specified in Section 4.
Prior to takeoff from fields above 3000 feet pressure altitude, the mixture
should be leaned to give maximum RPM in a full throttle, static run-up.
Decrease distances 10% for each 9 knots head wind. For operation with
tail winds up to 10 knots, increase distances by 10% for each 2 knots.
Where distance value have been deleted, climb performance is minimal.
For operation on dry grass runway, increase distances by 15% of the
“ground roll” figure.
Figure 5-5
172RPHBUS-00
U.S.
5-15
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
MAXIMUM RATE OF CLIMB
AT 2450 POUNDS
CONDITIONS:
Flaps UP
Full Throttle
Pressure
Altitude
Feet
Climb Speed
- KIAS
Rate of Climb - FPM
-20°C
0°C
20°C
40°C
Sea Level
79
830
770
705
640
2000
77
720
655
595
535
4000
76
645
585
525
465
6000
74
530
475
415
360
8000
72
420
365
310
250
10,000
71
310
255
200
145
12,000
69
200
145
---
---
NOTE
Mixture leaned above 3000 feet pressure altitude for
maximum RPM.
Figure 5-6
5-16
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
TIME, FUEL AND DISTANCE TO CLIMB
AT 2450 POUNDS
CONDITIONS:
Flaps UP
Full Throttle
Standard Temperature
Pressure
Altitude
Feet
Temp
From Sea Level
°C
Climb
Speed
KIAS
Rate of
Climb
FPM
Time
Minutes
Sea Level
15
79
720
0
0.0
0
1000
13
78
670
1
0.4
2
2000
11
77
625
3
0.7
4
3000
9
76
575
5
1.2
6
4000
7
76
560
6
1.5
8
5000
5
75
515
8
1.8
11
6000
3
74
465
10
2.1
14
7000
1
73
415
13
2.5
17
8000
-1
72
365
15
3.0
21
9000
-3
72
315
18
3.4
25
10,000
-5
71
270
22
4.0
29
11,000
-7
70
220
26
4.6
35
12,000
-9
69
170
31
5.4
43
Fuel Used Distance
Gallons
NM
NOTE
•
Add 1.1 gallons of fuel for engine start, taxi and takeoff
allowance.
•
Mixture leaned above 3000 feet pressure altitude for
maximum RPM.
•
Increase time, fuel and distance by 10% for each 10°C
above standard temperature.
•
Distances shown are based on zero wind.
Figure 5-7
172RPHBUS-00
U.S.
5-17
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CRUISE PERFORMANCE
CONDITIONS:
2450 Pounds
Recommended Lean Mixture
.
20°C BELOW
STANDARD
20°C ABOVE
Pressure
STANDARD
TEMP
TEMPERATURE
STANDARD
TEMP
Altitude RPM
%
%
%
Feet
MCP KTAS GPH MCP KTAS GPH MCP KTAS GPH
2000
2250
------79
115
9.0
74
114
8.5
2200 79
112
9.1
74
112
8.5
70
111
8.0
2100 69
107
7.9
65
106
7.5
62
105
7.1
2000 61
101
7.0
58
99
6.6
55
97
6.4
1900 54
94
6.2
51
91
5.9
50
89
5.8
4000
2300
2250
2200
2100
2000
1900
--80
75
66
58
52
--115
112
106
100
92
--9.2
8.6
7.6
6.7
6.0
79
75
70
62
55
50
117
114
111
105
98
90
9.1
8.6
8.1
7.1
6.4
5.8
75
70
66
59
53
49
117
114
110
103
95
87
8.6
8.1
7.6
6.8
6.2
5.6
6000
2350
2300
2250
2200
2100
2000
--80
76
71
63
56
--117
115
112
105
98
--9.2
8.7
8.1
7.2
6.4
80
75
71
67
60
53
120
117
114
111
104
96
9.2
8.6
8.1
7.7
6.9
6.2
75
71
67
64
57
52
119
116
113
109
101
93
8.6
8.1
7.7
7.3
6.6
6.0
NOTE
•
Maximum cruise power using recommended lean
mixture is 80% MCP. Power settings above 80% MCP
are listed to aid interpolation. Operations above 80%
MCP must use full rich mixture.
•
Cruise speeds are shown for an airplane equipped with
speed fairings. Without speed fairings, decrease speeds
shown by 2 knots.
Figure 5-8 (Sheet 1 of 2)
5-18
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
CRUISE PERFORMANCE
CONDITIONS:
2450 Pounds
Recommended Lean Mixture
.
20°C BELOW
STANDARD
20°C ABOVE
Pressure
STANDARD
TEMP
TEMPERATURE
STANDARD
TEMP
Altitude RPM
%
%
%
Feet
MCP KTAS GPH MCP KTAS GPH MCP KTAS GPH
8000
2400 ------80
122
9.2
76
121
8.7
2350 81
120
9.3
76
119
8.7
71
118
8.2
2300 76
117
8.7
71
116
8.2
68
115
7.8
2200 68
111
7.7
64
110
7.3
61
107
7.0
2100 60
104
6.9
57
102
6.6
55
99
6.4
2000 54
96
6.2
52
94
6.0
51
91
5.9
10,000
2350
2300
2250
2200
2100
2000
76
72
68
65
58
52
119
116
113
110
102
94
8.8
8.3
7.8
7.4
6.6
6.1
72
68
65
61
55
51
118
115
112
108
100
91
8.2
7.8
7.4
7.0
6.4
5.9
68
65
61
59
54
50
117
113
109
105
97
88
7.8
7.4
7.1
6.7
6.2
5.8
12,000
2350
2300
2250
2200
2100
73
69
65
62
56
119
115
112
108
100
8.3
7.9
7.5
7.1
6.4
69
65
62
59
54
117
113
109
105
97
7.9
7.5
7.1
6.8
6.2
65
62
59
57
53
115
111
107
103
94
7.5
7.1
6.8
6.6
6.1
NOTE
•
Maximum cruise power using recommended lean
mixture is 80% MCP. Power settings above 80% MCP
are listed to aid interpolation. Operations above 80%
MCP must use full rich mixture.
•
Cruise speeds are shown for an airplane equipped with
speed fairings. Without speed fairings, decrease speeds
shown by 2 knots.
Figure 5-8 (Sheet 2)
172RPHBUS-00
U.S.
5-19
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
RANGE PROFILE
45 MINUTES RESERVE
53 GALLONS USABLE FUEL
CONDITIONS:
2450 Pounds
Recommended Lean Mixture for Cruise at all altitudes
Standard Temperature
Zero Wind
NOTE
•
This chart allows for the fuel used for engine start, taxi, takeoff and
climb, and the distance during a normal climb.
•
Cruise speeds are shown for an airplane equipped with speed
fairings. Without speed fairings, decrease speeds shown by 2
knots.
Figure 5-9
5-20
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 5
PERFORMANCE
ENDURANCE PROFILE
45 MINUTES RESERVE
53 GALLONS USABLE FUEL
CONDITIONS:
2450 Pounds
Recommended Lean Mixture for Cruise at all altitudes
Standard Temperature
NOTE
This chart allows for the fuel used for engine start, taxi,
takeoff and climb, and the time during a normal climb.
Figure 5-10
172RPHBUS-00
U.S.
5-21
SECTION 5
PERFORMANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SHORT FIELD LANDING DISTANCE
AT 2450 POUNDS
CONDITIONS:
Flaps FULL
Power IDLE
Maximum Braking
Zero Wind
Paved, Level, Dry Runway
Speed at 50 ft: 62 KIAS
0°C
Pressure
Altitude
Feet
10°C
20°C
30°C
40°C
Total
Total
Total
Total
Total
Feet
Feet
Feet
Feet
Feet
Gnd
Gnd
Gnd
Gnd
Gnd
To
To
To
To
To
Roll Clear Roll Clear Roll Clear Roll Clear Roll Clear
Feet 50 Feet 50 Feet 50 Feet 50 Feet 50
Foot
Foot
Foot
Foot
Foot
Obst
Obst
Obst
Obst
Obst
Sea Level
525
1250
540
1280
560
1310
580
1340
600
1370
1000
545
1280
560
1310
580
1345
600
1375
620
1405
2000
565
1310
585
1345
605
1375
625
1410
645
1440
3000
585
1345
605
1380
625
1415
650
1445
670
1480
4000
605
1380
630
1415
650
1450
670
1485
695
1520
5000
630
1415
650
1455
675
1490
700
1525
720
1560
6000
655
1455
675
1490
700
1530
725
1565
750
1605
7000
680
1495
705
1535
730
1570
755
1610
775
1650
8000
705
1535
730
1575
755
1615
780
1655
810
1695
NOTE
•
•
Short field technique as specified in Section 4.
•
For operation on dry grass runway, increase distances
by 45% of the “ground roll” figure.
•
If landing with flaps up, increase the approach speed by
7 KIAS and allow for 35% longer distances.
Decrease distances 10% for each 9 knots head wind.
For operation with tail winds up to 10 knots, increase
distances by 10% for each 2 knots.
Figure 5-11
5-22
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
WEIGHT AND BALANCE/
EQUIPMENT LIST
TABLE OF CONTENTS
Page
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3
Airplane Weighing Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3
Airplane Weighing Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-5
Sample Weight and Balance Record . . . . . . . . . . . . . . . . . . . . . . 6-7
Weight And Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-8
Baggage Tiedown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-9
Sample Loading Problem . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-10
Loading Graph . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-12
Loading Arrangements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-13
Internal Cabin Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-14
Center Of Gravity Moment Envelope . . . . . . . . . . . . . . . . . . . . . 6-15
Center of Gravity Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-16
Comprehensive Equipment List . . . . . . . . . . . . . . . . . . . . . . .6-17/6-18
172RPHBUS-00
U.S.
6-1/6-2
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
INTRODUCTION
This section describes the procedure for establishing the basic empty
weight and moment of the airplane. Sample forms are provided for
reference. Procedures for calculating the weight and moment for
various operations are also provided. For additional information
regarding Weight and Balance procedures, refer to the Aircraft Weight
and Balance Handbook (FAA-H-8083-1). A comprehensive list of
Cessna equipment available for this airplane is included at the back of
this section.
Specific information regarding the weight, arm, moment and installed
equipment for this airplane as delivered from the factory can be found
in the plastic envelope in the back of this POH.
WARNING
IT IS THE RESPONSIBILITY OF THE PILOT TO MAKE
SURE THE AIRPLANE IS LOADED PROPERLY.
OPERATION OUTSIDE OF PRESCRIBED WEIGHT AND
BALANCE LIMITATIONS COULD RESULT IN AN
ACCIDENT AND SERIOUS OR FATAL INJURY.
AIRPLANE WEIGHING PROCEDURES
1. Preparation:
a. Inflate tires to recommended operating pressures.
b. Defuel airplane. Refer to the Maintenance Manual.
c. Service engine oil as required to obtain a normal full
indication (approximately 7 quarts on dipstick).
d. Move sliding seats to the most forward position.
e. Raise flaps to the fully retracted position.
f. Place all control surfaces in neutral position.
g. Remove all non-required items from airplane.
(Continued Next Page)
172RPHBUS-00
U.S.
6-3
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AIRPLANE WEIGHING PROCEDURES (Continued)
2. Level:
a. Place scales under each wheel (minimum scale capacity,
1000 pounds).
b. Deflate the nose tire and/or lower or raise the nose strut to
properly center the bubble in the level (Refer to Figure 6-1
Sheet 1).
3. Weigh:
a. Weigh airplane in a closed hangar to avoid errors caused by
air currents.
b. With the airplane level and brakes released, record the
weight shown on each scale. Deduct the tare, if any, from
each reading.
4. Measure:
a. Obtain measurement A by measuring horizontally (along the
airplane centerline) from a line stretched between the main
wheel centers to a plumb bob dropped from the firewall.
b. Obtain measurement B by measuring horizontally and
parallel to the airplane centerline, from center of nosewheel
axle, left side, to a plumb bob dropped from the line between
the main wheel centers. Repeat on right side and average
the measurements.
5. Using weights from step 3 and measurements from step 4, the
Basic Empty Weight and C.G. can be determined by completing
Figure 6-1 (Sheet 2).
6. Changes to the Airplane Weight and Balance due to alteration or
repair must be documented in a permanent record within the
POH similar to that shown in Figure 6-2.
7. A new Basic Empty Weight and CG Arm based on actual
airplane weight (as weighed) is required after a major repair or
alteration. It is recommended that the airplane be weighed to
verify Basic Empty Weight and CG Arm at intervals not to
exceed 5 years.
6-4
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
AIRPLANE WEIGHING FORM
Figure 6-1 (Sheet 1 of 2)
172RPHBUS-00
U.S.
6-5
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AIRPLANE WEIGHING FORM
Figure 6-1 (Sheet 2)
6-6
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
SAMPLE WEIGHT AND BALANCE RECORD
Figure 6-2
172RPHBUS-00
U.S.
6-7
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
WEIGHT AND BALANCE
The following information will enable you to operate your Cessna within
the prescribed weight and center of gravity limitations. To determine
weight and balance, use the Sample Loading Problem (Figure 6-3),
Loading Graph (Figure 6-4), and Center of Gravity Moment Envelope
(Figure 6-7) as follows:
Enter the appropriate basic empty weight and moment/1000 from the
weight and balance records for your airplane in the YOUR AIRPLANE
column of the Sample Loading Problem.
NOTE
In addition to the basic empty weight and moment noted on
these records, the C.G. arm (FS) is also shown, but need
not be used on the Sample Loading Problem. The moment
which is shown must be divided by 1000 and this value
used as the moment/1000 on the loading problem.
Use the Loading Graph to determine the moment/1000 for each
additional item to be carried; then list these on the loading problem.
NOTE
Loading Graph information for the pilot, passengers and
baggage is based on seats positioned for average
occupants and baggage loaded in the center of the
baggage areas as shown on the Loading Arrangements
diagram. For loadings which may differ from these, the
Sample Loading Problem lists fuselage stations (FS) for
these items to indicate their forward and aft C.G. range
limitations (seat travel and baggage area limitation). Refer
to Figures 6-5 and 6-6 for additional loading information.
Additional moment calculations, based on the actual weight
and C.G. arm (FS) of the item being loaded, must be made
if the position of the load is different from that shown on the
Loading Graph.
Total the weights and moments/1000 and plot these values on the
Center of Gravity Moment Envelope to determine whether the point
falls within the envelope, and if the loading is acceptable.
(Continued Next Page)
6-8
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
WEIGHT AND BALANCE (Continued)
BAGGAGE TIEDOWN
A nylon baggage net having four tiedown straps is provided as
standard equipment to secure baggage on the cabin floor aft of the rear
seat (baggage area A) and in the aft baggage area (baggage area B).
Six eyebolts serve as attaching points for the net. Two eyebolts for the
forward tiedown straps are mounted on the cabin floor near each
sidewall just forward of the baggage door approximately at station FS
90; two eyebolts are installed on the cabin floor slightly inboard of each
sidewall approximately at FS 107; and two eyebolts are located below
the aft window near each sidewall approximately at FS 107. A placard
on the baggage door defines the weight limitations in the baggage
areas.
When baggage area A is utilized for baggage only, the two forward floor
mounted eyebolts and the two aft floor mounted eyebolts (or the two
eyebolts below the aft window) may be used, depending on the height
of the baggage. When baggage is carried in the baggage area B only,
the aft floor mounted eyebolts and the eyebolts below the aft window
should be used. When baggage is loaded in both areas, all six eyebolts
should be utilized.
172RPHBUS-00
U.S.
6-9
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SAMPLE LOADING PROBLEM
WEIGHT AND MOMENT
TABULATION
ITEM DESCRIPTION
SAMPLE
AIRPLANE
YOUR
AIRPLANE
Weight Moment Weight Moment
(lbs)
(lb-ins/
(lbs)
(lb-ins/
1000)
1000)
1 - Basic Empty Weight
(Use the data pertaining to your airplane
as it is presently equipped. Includes
unusable fuel and full oil)
1639
64.4
210
10.1
3 - Pilot and Front Passenger (FS 34 to 46)
340
12.6
4 - Rear Passengers (FS 73)
220
16.0
5 - *Baggage “A” (FS 82 to 108)
120 Pounds Maximum
48
4.6
7 - RAMP WEIGHT AND MOMENT
2457
107.7
8 - Fuel allowance for engine start, taxi and
runup
-7.0
-0.3
9 - TAKEOFF WEIGHT AND MOMENT
(Subtract Step 8 from Step 7)
2450
107.4
2 - Usable Fuel (At 6 Lbs./Gal.)
- Standard Fuel - 53 Gallons Maximum
- Reduced Fuel - 35 Gallons
6 - *Baggage “B” (FS 108 to 142)
50 Pounds Maximum
10 - Locate this point (2450 at 107.4) on the Center of Gravity Moment Envelope,
and since this point falls within the envelope, the loading is acceptable.
*The maximum allowable combined weight capacity for baggage in areas “A”
and “B” is 120 pounds.
Figure 6-3 (Sheet 1 of 2)
6-10
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
SAMPLE LOADING PROBLEM
NOTE
When several loading configurations are representative of
your operations, it may be useful to fill out one or more of
the above columns so specific loadings are available at a
glance.
Figure 6-3 (Sheet 2)
172RPHBUS-00
U.S.
6-11
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
LOADING GRAPH
NOTE
Line representing adjustable seats shows the pilot and
front seat passenger center of gravity on adjustable seats
positioned for average occupant. Refer to the Loading
Arrangements diagram for forward and aft limits of
occupant C.G. range.
Figure 6-4
6-12
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
LOADING ARRANGEMENTS
*Pilot and front seat passenger center of gravity on adjustable seats
positioned for average occupant. Numbers in parentheses indicate
forward and aft limits of occupant center of gravity range.
**Arm measured to the center of the areas shown.
NOTE
•
•
The usable fuel C.G. arm is located at FS 48.00.
•
To achieve an airplane loading within the utility category,
it may be necessary to remove the rear passenger seat
assembly from the airplane. Refer to Figure 6-9 for
applicable weight and arm.
The aft baggage wall (approximate FS 108.00) or aft
baggage wall (approximate FS 142.00) can be used as
a convenient interior reference point for determining the
location of baggage area fuselage stations.
Figure 6-5
172RPHBUS-00
U.S.
6-13
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
INTERNAL CABIN DIMENSIONS
NOTE
•
Maximum allowable floor loading is 200 pounds per
square foot.
•
All dimensions shown are in inches.
Figure 6-6
6-14
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
CENTER OF GRAVITY MOMENT ENVELOPE
Figure 6-7
172RPHBUS-00
U.S.
6-15
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CENTER OF GRAVITY LIMITS
Figure 6-8
6-16
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
COMPREHENSIVE EQUIPMENT LIST
Figure 6-9 is a comprehensive list of all Cessna equipment which is available for
the Model 172R airplane equipped with Garmin G1000 Integrated Cockpit System
and GFC 700 Autopilot (if installed) (Serials 17281497 and On). This
comprehensive equipment list provides the following information in column form:
In the ITEM NO column, each item is assigned a coded number. The first two
digits of the code represent the identification of the item within Air Transport
Association Specification 100 (11 for Paint and Placards; 24 for Electrical
Power; 77 for Engine Indicating, etc.). These assignments also correspond to
the Maintenance Manual chapter for the airplane. After the first two digits, items
receive a unique sequence number (01, 02, 03, etc.). After the sequence
number, a suffix letter is assigned to identify equipment as a required item, a
standard item or an optional item.
Suffix letters are as follows:
R = Required items or equipment for FAA certification (14 CFR 23 or 14
CFR 91).
S = Standard equipment items.
O = Optional equipment items replacing required or standard items.
A = Optional equipment items which are in addition to required or
standard items.
In the EQUIPMENT LIST DESCRIPTION column, each item is assigned a
descriptive name to help identify its function.
In the REF DRAWING column, a Cessna drawing number is provided which
corresponds to the item.
NOTE
If additional equipment is to be installed, it must be done in
accordance with the reference drawing, service bulletin or a separate
FAA approval.
In the WT LBS and ARM INS columns, information is provided on the weight (in
pounds) and arm (in inches) of the equipment item.
NOTE
•
Unless otherwise indicated, true values (not net change values)
for the weight and arm are shown. Positive arms are distances aft
of the airplane datum; negative arms are distances forward of the
datum.
•
Asterisks (*) in the weight and arm column indicate complete
assembly installations. Some major components of the assembly
are listed on the lines immediately following. The sum of these
major components does not necessarily equal the complete
assembly installation.
172RPHBUS-00
U.S.
6-17/6-18
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ITEM NO
11-01-S
21-01-S
21-02-S
21-03-R
21-04-R
22-01-O
23-01-S
23-02-R
23-03-R
23-04-S
24-01-R
24-02-R
24-03-R
24-04-S
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
REF
DRAWING
EQUIPMENT LIST DESCRIPTION
11 - PAINT AND PLACARDS
PAINT, OVERALL WHITE WITH COLOR STRIPE
- OVERALL WHITE COLOR
- COLOR STRIPING
21 - AIR CONDITIONING
VENTILATORS, ADJUSTABLE, CABIN AIR
CABIN HEATER SYSTEM, SHROUDED MUFFLER
TYPE
FORWARD AVIONICS COOLING FAN - MC24B3
AFT AVIONICS COOLING FAN
22 - AUTO FLIGHT
GFC 700 AUTOPILOT
- PITCH SERVO
- PITCH TRIM SERVO
- ROLL SERVO
23 - COMMUNICATIONS
STATIC DISCHARGE WICKS, (SET OF 10)
AUDIO/INTERCOM/MARKER BEACON
- GMA 1347 AUDIO PANEL
- CI-102 MARKER BEACON ANTENNA
NAV/COM/GPS #1 COMPUTER
- GIA 63W INTEGRATED AVIONICS UNIT
- CI 2580-200 VHF COMM/GPS ANTENNA
NAV/COM/GPS #2 COMPUTER
- GIA 63W INTEGRATED AVIONICS UNIT
- CI 2580-200 VHF COMM/GPS ANTENNA
- CI 420-10 XM ANTENNA
24 - ELECTRICAL POWER
ALTERNATOR, 28 VOLT, 60 AMP, - 9910591-11
BATTERY, 24 VOLT, 8.0 AMP HOUR
POWER DISTRIBUTION MODULE - S3100-366
- ALTERNATOR CONTROL UNIT - AC2101
- MASTER CONTACTOR - X61-0007
- STARTER CONTACTOR - X61-0027
- AMMETER TRANSDUCER - CS3200
BATTERY, STANDBY - AVT 200413
WT ARM
LBS INS.
0500531
19.2*
18.4
0.8
95.4*
91.5
135.9
0513575-2
0550365
1.7
2.5
60.0
-20.75
3930379
3940397
0.5
1.1
12.7
109.0
3940475
3940475
3940474
6.9
2.3
2.3
2.3
118.5
150.6
150.6
54.2
0501048-1
0.4
143.2
320317
3960188
3921165
3940397
3960220
3921165
3940397
3960220
3960233
1.7
0.5
16.3
129.0
4.9
0.5
113.3
61.2
4.9
0.5
0.5
113.3
61.2
43.5
0550365
0518034
0518034
53100-366
53100-366
53100-366
53100-366
0518025
10.0
23.2
6.4*
0.2
0.7
0.7
0.1
14.0
-29.0
-5.0
-2.5*
-2.5
-2.5
-2.5
-2.0
11.2
Figure 6-9 (Sheet 1 of 6)
172RPHBUS-00
U.S.
6-19
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
ITEM NO
25-01-R
25-02-O
25-03-S
25-04-O
25-05-S
25-06-O
25-07-R
25-08-S
25-09-S
25-10-S
25-11-S
25-12-S
25-13-R
25-14-R
25-15-O
25-16-S
25-17-S
25-18-O
EQUIPMENT LIST DESCRIPTION
25 - EQUIPMENT/FURNISHINGS
SEAT, PILOT, ADJUSTABLE, CLOTH/VINYL
COVER
SEAT, PILOT, ADJUSTABLE, LEATHER/VINYL
COVER
SEAT, FRONT PASSENGER, ADJUSTABLE,
CLOTH/VINYL COVER
SEAT, FRONT PASSENGER, ADJUSTABLE,
LEATHER/VINYL COVER
SEAT, REAR PASSENGER, ONE-PIECE BACK,
CLOTH/VINYL COVER
SEAT, REAR PASSENGER, ONE-PIECE BACK,
LEATHER/VINYL COVER
SEAT BELT AND SHOULDER HARNESS, INERTIA
REEL, AUTO ADJUST, PILOT AND FRONT
PASSENGER
SEAT BELT AND SHOULDER HARNESS, INERTIA
REEL, AUTO ADJUST, REAR SEAT
SUN VISOR (SET OF 2)
BAGGAGE RESTRAINT NET
CARGO TIEDOWN RINGS (SET OF 6)
TOW BAR, NOSE GEAR (STOWED)
PILOT'S OPERATING HANDBOOK AND FAA
APPROVED
AIRPLANE
FLIGHT
MANUAL
(STOWED IN FRONT PASSENGER'S SEAT BACK)
GARMIN G1000 COCKPIT REFERENCE GUIDE
(STOWED IN COCKPIT SIDE PANEL POCKET)
APPROACH PLATE HOLDER
FUEL SAMPLING CUP (STOWED IN PILOT’S
SEAT BACK)
ARTEX ME406 - 2 FREQUENCY ELT
- ELT TRANSMITTER
- ANTENNA AND CABLE ASSY
ARTEX C406-N - 3 FREQUENCY ELT
- ELT TRANSMITTER
- ANTENNA AND CABLE ASSY
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
REF
DRAWING
WT ARM
LBS INS.
0719025-1
33.8
41.5
0719025-4
34.3
41.5
0719025-1
33.8
41.5
0719025-4
34.3
41.5
0719028-1
50.0
82.0
0719028-2
51.0
82.0
0519031-1
5.2
50.3
0519031-1
5.2
87.8
0514166-2
2015009-7
0515055-6
0501019-1
0500832-1
1.1
0.5
0.2
1.7
2.2
32.8
95.0
95.0
124.0
50.0
1.5
15.0
0715083-1
S2107-1
0.1
0.1
22.0
50.0
3940458-1
ME406
110-338
3940460-1
C406-N
110-338
2.6*
2.1
0.5
5.1*
4.6
0.5
134.6*
135.5
130.0
135.0*
135.5
130.0
Figure 6-9 (Sheet 2)
6-20
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ITEM NO
26-01-S
27-01-S
27-02-A
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
EQUIPMENT LIST DESCRIPTION
REF
DRAWING
WT ARM
LBS INS.
26 - FIRE PROTECTION
FIRE EXTINGUISHER
- FIRE EXTINGUISHER, HAND TYPE
- MOUNTING CLAMP AND HARDWARE
0501011-2
A352GS
1290010-1
5.3*
4.8
0.5
43.0*
44.0
42.2
27 - FLIGHT CONTROLS
DUAL CONTROLS, RIGHT SEAT
- CONTROL WHEEL, COPILOT
- RUDDER AND BRAKE PEDAL, COPILOT
RUDDER PEDAL EXTENSION (SET OF 2)
0506008-1
0513576-4
0510402-16
0501082-1
5.5*
2.6
1.1
2.9
12.4*
26.0
6.8
8.0
(INSTALLED ARM SHOWN)
28-01-R
28-02-R
28 - FUEL
AUXILIARY FUEL PUMP - 5100-00-4
FUEL SENDER - 76-207-3
0516015
0522644
1.9
0.9
9.5
47.4
30-01-S
30 - ICE AND RAIN PROTECTION
PITOT HEAT
0523080
0.1
28.0
0506009
0523112
3930377
0518006
0.5
0.4
2.2
0.1
16.1
28.5
11.4
41.5
0541200-7, -8
C163001-0104
C163030-0111
C262003-0101
C262023-0102
0543062-17
1241156-12
C262003-0202
C262023-0101
0541225-1
0543079-3
0541223-1, -2
0541224-1, -2
0541220-1, -2
34.4*
6.2
1.8
7.9
1.3
9.5*
3.5
4.6
1.4
16.5*
3.5
10.1
1.1
0.8
57.8*
58.2
54.5
58.2
58.2
-6.8*
-6.8
-6.8
-6.8
48.1*
-3.5
61.1
55.6
59.5
31-01-S
31-02-R
31-03-R
31-04-R
32-01-R
32-02-R
32-03-S
31 - INDICATING/RECORDING SYSTEM
RECORDING HOURMETER - C664503-0103
PNEUMATIC STALL WARNING SYSTEM
GEA 71 ENGINE/AIRFRAME UNIT
GTP 59 OUTSIDE AIR TEMPERATURE (OAT)
PROBE
32 - LANDING GEAR
WHEEL BRAKE AND TIRE, 6.00 X 6 MAIN (2)
- WHEEL ASSY (EACH)
- BRAKE ASSY (EACH)
- TIRE, 4-PLY, 6.00 X 6, BLACKWALL (EACH)
- TUBE, (EACH)
WHEEL AND TIRE ASSY, 5.00 X 5 NOSE
- WHEEL ASSY
- TIRE, 6-PLY, 5.00 X 5, BLACKWALL
- TUBE
WHEEL FAIRING AND INSTALLATION
- WHEEL FAIRING, NOSE
- WHEEL FAIRINGS, MAIN (SET OF 2)
- BRAKE FAIRINGS (SET OF 2)
- MOUNTING PLATE (SET OF 2)
Figure 6-9 (Sheet 3)
172RPHBUS-00
U.S.
6-21
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
ITEM NO
33-01-S
33-02-S
33-03-S
33-04-R
33-05-S
34-01-R
34-02-R
34-03-R
34-04-S
34-05-R
34-06-R
34-07-R
34-08-R
34-09-R
34-10-R
34-11-S
34-12-O
34-13-O
EQUIPMENT LIST DESCRIPTION
33 - LIGHTS
MAP LIGHT IN CONTROL WHEEL
COURTESY LIGHTS UNDER WING
FLASHING BEACON
STROBE LIGHT
LANDING AND TAXI LIGHT
34 - NAVIGATION
STANDBY AIRSPEED INDICATOR - S3325-1
STANDBY ATTITUDE INDICATOR - S3326-2
STANDBY ALTIMETER, SENSITIVE WITH 20
FOOT MARKINGS, INCHES OF MERCURY AND
MILLBARS - S3827-1
ALTERNATE STATIC AIR SOURCE
COMPASS, MAGNETIC
TRANSPONDER
- GTX-33 TRANSPONDER
- CI 105-16 TRANSPONDER ANTENNA
PFD DISPLAY
- GDU DISPLAY
MFD DISPLAY
- GDU DISPLAY
ATTITUDE HEADING REFERENCE SENSOR
(AHRS)
- GRS 77 AHRS
- GMU 44 MAGNETOMETER
AIR DATA COMPUTER
- GDC 74A AIR DATA COMPUTER
GDL-69A DATALINK
AUTOMATIC DIRECTION FINDER (ADF)
- KR 87 ADF RECEIVER
- ADF ANTENNA
DISTANCE MEASURING EQUIPMENT (DME)
- KN 63 REMOTE DME
- CI 105-16 DME ANTENNA
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
REF
DRAWING
WT ARM
LBS INS.
0706015
0521101-8
0506003-6
0723628
0523029-7
0.2
0.5
1.4
3.4
2.4
21.5
61.0
240.7
43.3
28.7
0506009
0501135
0506009
0.7
2.2
0.9
16.2
14.0
14.0
0501017-1
0513262-3
3940397
3910317
3960191
3930377
3910317
3930377
3910317
3940397
0.2
0.5
15.5
18.0
3.6
0.4
134.0
86.3
6.3
16.4
6.3
16.4
3910317
3940398
3940397
3910317
3940397
2.4
0.4
134.0
52.7
1.7
1.9
11.4
112.8
3930494
3960187
3.2
4.2
12.1
39.3
3940448
3960231
2.8
0.4
154.0
114.5
Figure 6-9 (Sheet 4)
6-22
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ITEM NO
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
EQUIPMENT LIST DESCRIPTION
REF
DRAWING
WT ARM
LBS INS.
37-02-R
37 - VACUUM
ENGINE DRIVEN VACUUM PUMP
- VACUUM PUMP - AA3215CC
- COOLING SHROUD
- FILTER
- VACUUM REGULATOR
VACUUM TRANSDUCER - P165-5786
0501135
1201998-1
1201075-2
AA2H3-2
0501135
2.1
0.2
0.3
0.5
0.3
-5.0
-5.6
2.0
2.0
10.3
53-01-S
53 - FUSELAGE
REFUELING STEPS AND HANDLE
0513415-2
1.7
16.3
56-01-S
56-02-S
56 - WINDOWS
WINDOW, HINGED RIGHT SIDE (NET CHANGE)
WINDOW, HINGED LEFT SIDE (NET CHANGE)
0517001-40
0517001-39
2.3*
2.3*
48.0
48.0
37-01-R
61-01-R
61-02-R
71-01-R
71-02-O
72-01-R
61 - PROPELLER
FIXED PITCH PROPELLER ASSEMBLY
- MCCAULEY 75 INCH PROPELLER
- MCCAULEY 3.5 INCH PROPELLER SPACER
SPINNER INSTALLATION, PROPELLER
- SPINNER DOME ASSEMBLY
- FWD SPINNER BULKHEAD
- AFT SPINNER BULKHEAD
71 - POWERPLANT
FILTER, INDUCTION AIR
WINTERIZATION KIT INSTALLATION (STOWED)
(INSTALLED ARM SHOWN)
- BREATHER TUBE INSULATION
- COWL INLET COVERS (INSTALLED)
- COWL INLET COVERS (STOWED)
72 - ENGINES
ENGINE, LYCOMING IO-360-L2A
0550320-18
38.8*
IC235/LFA7570 35.0
C5464
3.6
0550320-11
1.8*
0550236-14
1.0
0552231-1
0.3
0550321-10
0.4
-38.2*
-38.4
-36.0
-41.0*
-42.6
-40.8
-37.3
0550365
0501128-3
-27.5
-20.3*
0.3
0.8*
0552011
0.4
0552229-3, -4 0.3
0552229-3, -4 0.3
0550365
-13.8
-32.0
95.0
297.8* -18.6*
Figure 6-9 (Sheet 5)
172RPHBUS-00
U.S.
6-23
SECTION 6
WEIGHT AND BALANCE/
EQUIPMENT LIST
ITEM NO
73-01-R
77-01-R
77-02-S
77-03-S
78-01-R
79-01-R
79-02-R
79-03-R
EQUIPMENT LIST DESCRIPTION
73 - ENGINE FUEL AND CONTROL
FUEL FLOW TRANDUCER - 680501K
77 - ENGINE INDICATING
ENGINE TACHOMETER SENSOR - 1A3C-2
CYLINDER HEAD THERMOCOUPLES
(ALL CYLINDERS) - 32DKWUE006F0126
EXHAUST THERMOCOUPLES
(ALL CYLINDERS) - 86317
78 - EXHAUST
EXHAUST SYSTEM
- MUFFLER AND TAILPIPE WELD ASSEMBLY
- SHROUD ASSEMBLY, MUFFLER HEATER
79 - OIL
OIL COOLER - 10877A
OIL PRESSURE SENSOR - P165-5281
OIL TEMPERATURE SENSOR - S2335-1
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
REF
DRAWING
WT ARM
LBS INS.
0501168
0.8
-22.6
0501168
0501168
0.2
0.2
-8.0
-12.0
0501168
0.3
-12.0
9954100-1
9954100-2
9954100-3
16.3*
4.6
0.8
-20.0*
-22.7
-22.7
0550365
0550365
0550365
2.3
0.2
0.2
-11.0
-12.9
-8.5
Figure 6-9 (Sheet 6)
6-24
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
AIRPLANE AND SYSTEMS DESCRIPTION
TABLE OF CONTENTS
Page
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-5
Airframe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-5
Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-7
Trim Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-7
Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-10
Pilot Panel Layout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-10
Center Panel Layout. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-11
Right Panel Layout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-13
Center Pedestal Layout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-13
Flight Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-16
Attitude Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-17
Airspeed Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-18
Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-18
Horizontal Situation Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-19
Vertical Speed Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-20
Ground Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-21
Wing Flap System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-22
Landing Gear System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23
Baggage Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23
Seats . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-24
Integrated Seat Belt/Shoulder Harness . . . . . . . . . . . . . . . . . . . . . . 7-25
Entrance Doors And Cabin Windows . . . . . . . . . . . . . . . . . . . . . . . 7-27
Control Locks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-28
Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-29
Engine Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-29
Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-30
RPM (Tachometer) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-31
Fuel Flow . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-32
Oil Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-32
Oil Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-33
(Continued Next Page)
172RPHBUS-00
U.S.
7-1
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
TABLE OF CONTENTS (Continued)
Page
Cylinder Head Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Exhaust Gas Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
New Engine Break-In And Operation . . . . . . . . . . . . . . . . . . . . .
Engine Lubrication System . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Ignition And Starter System. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Air Induction System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Exhaust System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Injection System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Cooling System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Distribution. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Indicating System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Calculations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Auxiliary Fuel Pump Operation . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Return System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Venting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Reduced Tank Capacity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Selector Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Drain Valves . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Brake System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
G1000 Annunciator Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Master Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Standby Battery Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Avionics Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Electrical System Monitoring And Annunciations . . . . . . . . . . . .
Bus Voltage (Voltmeters) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Ammeters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Standby Battery Annunciation . . . . . . . . . . . . . . . . . . . . . . . . . . .
Low Voltage Annunciation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
High Voltage Annunciation . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Circuit Breakers And Fuses. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
External Power Receptacle . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-34
7-34
7-35
7-35
7-36
7-36
7-37
7-37
7-37
7-37
7-38
7-39
7-39
7-41
7-43
7-44
7-44
7-44
7-45
7-46
7-46
7-47
7-51
7-51
7-52
7-52
7-53
7-53
7-54
7-54
7-55
7-56
7-57
7-58
(Continued Next Page)
7-2
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
TABLE OF CONTENTS (Continued)
Page
Lighting Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-59
Exterior Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-59
Interior Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-60
Cabin Heating, Ventilating And Defrosting System . . . . . . . . . . . . . 7-62
Pitot-Static System And Instruments . . . . . . . . . . . . . . . . . . . . . . . . 7-64
Vacuum System And Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . 7-65
Attitude Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-65
Vacuum Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-65
Low Vacuum Annunciation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-65
Clock/O.A.T. Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-67
Stall Warning System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-67
Standard Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-68
Garmin Display Units (GDU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-68
Audio Panel (GMA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-69
Integrated Avionics Unit (GIA) . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-69
Attitude and Heading Reference System (AHRS)
and Magnetometer (GRS). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-69
Air Data Computer (GDC) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-70
Engine Monitor (GEA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-70
Transponder (GTX) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-70
XM Weather and Radio Data Link (GDL) . . . . . . . . . . . . . . . . . . . 7-70
GFC 700 Automatic Flight Control System (AFCS) (if installed) . 7-71
Control Wheel Steering (CWS) . . . . . . . . . . . . . . . . . . . . . . . . . . 7-71
Avionics Support Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-73
Avionics Cooling Fans . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-73
Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-74
Microphone And Headset Installations. . . . . . . . . . . . . . . . . . . . . 7-75
Auxiliary Audio Input Jack . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-76
12V Power Outlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-77
Static Dischargers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-78
Cabin Features . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-79
Emergency Locator Transmitter (ELT) . . . . . . . . . . . . . . . . . . . . . 7-79
Cabin Fire Extinguisher . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-79
Carbon Monoxide Detection System . . . . . . . . . . . . . . . . . . . . . . 7-80
172RPHBUS-00
U.S.
7-3/7-4
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
INTRODUCTION
This section provides description and operation of the airplane and its
systems. Some equipment described herein is optional and may not be
installed in the airplane. Refer to Section 9, Supplements, for details of
other optional systems and equipment.
AIRFRAME
The airplane is an all metal, four-place, high wing, single-engine
airplane equipped with tricycle landing gear and is designed for general
utility and training purposes.
The construction of the fuselage is a conventional formed sheet metal
bulkhead, stringer, and skin design referred to as semimonocoque.
Major items of structure are the front and rear carry through spars to
which the wings are attached, a bulkhead and forgings for main landing
gear attachment at the base of the rear door posts, and a bulkhead with
attach fittings at the base of the forward door posts for the lower
attachment of the wing struts. Four engine mount stringers are also
attached to the forward door posts and extend forward to the firewall.
The externally braced wings, containing integral fuel tanks, are
constructed of a front and rear spar with formed sheet metal ribs,
doublers, and stringers. The entire structure is covered with aluminum
skin. The front spars are equipped with wing-to-fuselage and wing-tostrut attach fittings. The aft spars are equipped with wing-to-fuselage
attach fittings, and are partial span spars. Conventional hinged ailerons
and single slot type flaps are attached to the trailing edge of the wings.
The ailerons are constructed of a forward spar containing balance
weights, formed sheet metal ribs and V type corrugated aluminum skin
joined together at the trailing edge. The flaps are constructed basically
the same as the ailerons, with the exception of the balance weights and
the addition of a formed sheet metal leading edge section.
The empennage (tail assembly) consists of a conventional vertical
stabilizer, rudder, horizontal stabilizer, and elevator. The vertical
stabilizer consists of a spar, formed sheet metal ribs and
reinforcements, a wraparound skin panel, formed leading edge skins
and a dorsal.
(Continued Next Page)
172RPHBUS-00
U.S.
7-5
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AIRFRAME (Continued)
The rudder is constructed of a formed leading edge skin and spar with
attached hinge brackets and ribs, a center spar, a wrap around skin,
and a ground adjustable trim tab at the base of the trailing edge. The
top of the rudder incorporates a leading edge extension which contains
a balance weight.
The horizontal stabilizer is constructed of a forward and aft spar, ribs
and stiffeners, center, left, and right wrap around skin panels, and
formed leading edge skins. The horizontal stabilizer also contains the
elevator trim tab actuator.
Construction of the elevator consists of formed leading edge skins, a
forward spar, aft channel, ribs, torque tube and bellcrank, left upper and
lower "V" type corrugated skins, and right upper and lower "V" type
corrugated skins incorporating a trailing edge cutout for the trim tab.
The elevator tip leading edge extensions incorporate balance weights.
The elevator trim tab consists of a spar, rib, and upper and lower "V"
type corrugated skins.
7-6
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
FLIGHT CONTROLS
The airplane's flight control system, Refer to Figure 7-1, consists of
conventional aileron, rudder, and elevator control surfaces. The control
surfaces are manually operated through cables and mechanical linkage
using a control wheel for the ailerons and elevator, and rudder/brake
pedals for the rudder.
TRIM SYSTEMS
A manually operated elevator trim system is provided on this airplane,
Refer to Figure 7-1. Elevator trimming is accomplished through the
elevator trim tab by utilizing the vertically mounted trim control wheel on
the center pedestal. Forward rotation of the trim wheel will trim nose
down, conversely, aft rotation will trim nose up.
(Continued Next Page)
172RPHBUS-00
U.S.
7-7
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FLIGHT CONTROLS AND TRIM SYSTEM
Figure 7-1 (Sheet 1 of 2)
7-8
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
FLIGHT CONTROLS AND TRIM SYSTEMS
Figure 7-1 (Sheet 2)
172RPHBUS-00
U.S.
7-9
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
INSTRUMENT PANEL
The instrument panel, Refer to Figure 7-2, is of all metal construction
and is installed in sections so equipment can be easily removed for
maintenance. The glareshield, above and projecting aft from the
instrument panel, limits undesirable reflections on the windshield from
lighted equipment and displays mounted in the instrument panel.
The Nav III instrument panel contains the Garmin Display Unit (GDU)
Primary Flight Display (PFD) and Multifunction Display (MFD) and the
Garmin Audio Panel. For specific details regarding the instruments,
switches, circuit breakers and controls on the instrument panel, refer to
the related topics in this section.
PILOT PANEL LAYOUT
The PFD, centered on the instrument panel in front of the pilot, shows
the primary flight instruments during normal operation. During engine
start, reversionary operation (MFD failure), or when the DISPLAY
BACKUP switch is selected, the Engine Indication System (EIS) is
shown on the PFD. Refer to the Garmin G1000 Cockpit Reference
Guide (CRG) for specific operating information.
The Standby Battery (STBY BATT) switch is found at the upper left
corner of the pilot instrument panel on an internally lighted subpanel.
The switch positions (ARM/OFF/TEST) select the standby battery
operating modes. The rocker-type MASTER and AVIONICS switches
are found immediately below the standby battery switch.
The controls for adjusting instrument panel, equipment, and pedestal
lighting are found together on the subpanel below the MASTER and
AVIONICS switches. See the INTERNAL LIGHTING paragraphs of this
section for more information.
(Continued Next Page)
7-10
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
INSTRUMENT PANEL (Continued)
PILOT PANEL LAYOUT (Continued)
Switches for the airplane electrical systems and equipment are found
on an internally lighted subpanel found below the lower left corner of
the PFD. Each switch is labeled for function and is ON when the handle
is in the up position. See the ELECTRICAL EQUIPMENT descriptions
in this section for further information.
The circuit breaker panel is found along the lower edge of the pilot's
instrument panel below the electrical equipment switch panel and pilot
control wheel column. Each circuit breaker is identified for the
equipment or function it controls and for the bus from which it receives
power. Lighting for this subpanel is controlled using the SW/CB
PANELS dimmer control. See the ELECTRICAL EQUIPMENT
descriptions in this section for further information.
CENTER PANEL LAYOUT
The Garmin audio panel is found on the upper half of the center
instrument panel, immediately to the right of the PFD. A pushbutton
switch labeled DISPLAY BACKUP, to manually select display reversion
mode, is found on the lower face of the audio panel. Refer to the
Garmin G1000 CRG for operating information.
The MFD is found on the upper center panel to the right of the audio
panel. The MFD depicts EIS information along the left side of the
display and shows navigation, terrain, lightning and traffic data on the
moving map. Flight management or display configuration information
can be shown on the MFD in place of the moving map pages. Refer to
the Garmin G1000 CRG for operating information.
(Continued Next Page)
172RPHBUS-00
U.S.
7-11
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
INSTRUMENT PANEL (Continued)
CENTER PANEL LAYOUT (Continued)
The standby instrument cluster is in the center instrument panel below
the audio panel. A conventional (mechanical) airspeed indicator and a
sensitive aneroid altimeter are on each side of the vacuum-powered
attitude indicator. The pitot-static instruments share the airplane pitot
head and static ports with the air data computer. The attitude indicator
features a low vacuum flag to provide immediate warning of vacuum
system failure.
The engine controls are found on the lower center instrument panel
below the standby instrument cluster. The controls are conventional
push-pull-type controls for throttle and mixture. See ENGINE
description in this section for operating information.
The alternate static air valve is found adjacent to the throttle control.
Refer to the PITOT-STATIC SYSTEM AND INSTRUMENTS description
in this section for operating information.
The wing flap control lever and indicator are found at the lower right
side of the center panel. Refer to the WING FLAP SYSTEM description
in this section for operating information.
(Continued Next Page)
7-12
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
INSTRUMENT PANEL (Continued)
RIGHT PANEL LAYOUT
The Emergency Locator Transmitter (ELT) remote switch (ON/ARM/
TEST RESET) is positioned at the upper inboard corner of the right
panel adjacent to the MFD. Refer to Section 9, Supplements 1 or 2 for
appropriate ELT operating information.
The Hour (Hobbs) meter is found to the right of the ELT switch and
records engine operating time, when oil pressure is greater than 20
PSI, for maintenance purposes. Refer to the ENGINE INSTRUMENTS
description in this section for further information.
CENTER PEDESTAL LAYOUT
The center pedestal, located below the center panel, contains the
elevator trim control wheel, trim position indicator, 12V power outlet,
aux audio input jack, fuel shutoff valve, and the hand-held microphone.
The fuel selector valve handle is located at the base of the pedestal.
172RPHBUS-00
U.S.
7-13
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
INSTRUMENT PANEL
Figure 7-2
7-14
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
INSTRUMENT PANEL
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
26.
27.
28.
29.
30.
31.
32.
33.
34.
MASTER Switch (ALT and BAT)
STBY BATT Switch
STBY BATT Test Annunciator
AVIONICS Switch (BUS 1 and BUS 2)
Primary Flight Display
Standby Airspeed Indicator
Audio Control Panel
Standby Attitude Indicator
Standby Altimeter
Multifunction Display
ELT Remote Switch/Annunciator
Flight Hour Recorder
Bendix/King KR87 Automatic Direction Finder (if installed)
Microphone Button
Glove Box
Cabin Heat Control
Cabin Air Control
Wing Flap Control Lever And Position Indicator
Mixture Control Knob
Handheld Microphone
Fuel Shutoff Valve
Fuel Selector Valve
12V/10A Power Outlet
Aux Audio Input Jack
Elevator Trim Control Wheel And Position Indicator
Throttle Control Knob (With Friction Lock)
Go-Around Button
ALT Static Air Valve Control
Yoke Mounted Map Light
Parking Brake Handle
Circuit Breaker Panel
Electrical Switch Panel
MAGNETOS/START Switch
DIMMING Panel
172RPHBUS-00
U.S.
7-15
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FLIGHT INSTRUMENTS
The G1000 Integrated Cockpit System primary flight instrument
indications are shown on the PFD. The primary flight instruments are
arranged on the PFD in the basic T configuration. The Attitude Indicator
(AI) and Horizontal Situation Indicator (HSI) are centered vertically on
the PFD and are conventional in appearance and operation. Vertical
tape-style (scrolling scale) indicators with fixed pointers and digital
displays, show airspeed, altitude, and vertical speed. The vertical
indicators take the place of analog indicators with a fixed circular scale
and rotating pointer.
Knobs, knob sets (two knobs on a common shaft) and membrane type
push button switches, found on the bezel surrounding each GDU
display, control COM, NAV, XPDR, AUTOPILOT (if installed) and GPS
avionics, set BARO (barometric pressure), CRS (course), and HDG
(heading), and work various flight management functions. Some push
button switches are dedicated to certain functions (keys) while other
switches have functions defined by software (softkeys). A softkey may
perform various operations or functions at various times based on
software definition. Softkeys are found along the lower bezel of the
GDU displays.
(Continued Next Page)
7-16
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
FLIGHT INSTRUMENTS (Continued)
ATTITUDE INDICATOR
The G1000 attitude indicator is shown on the upper center of the PFD.
The attitude indication data is provided by the Attitude and Heading
Reference System (AHRS). The G1000 attitude indicator provides a
horizon line that is the full width of the GDU display.
The roll index scale is conventional with 10° graduations to 30° and
then 15° graduations to 60° of roll. The roll pointer is slaved to the
airplane symbol. The pitch index scale is graduated in 5° increments
with every 10° of pitch labeled. If pitch limits are exceeded in either the
nose-up or nose-down direction, red warning chevrons will appear on
the indicator to point the way back to level flight. A small white
trapezoid located below the roll pointer moves laterally left and right to
provide the slip-skid information previously supplied by the skid
indicator ball. The trapezoid should be centered below the roll pointer
for coordinated turns. The standby (vacuum) attitude indicator is found
on the lower center instrument panel.
(Continued Next Page)
172RPHBUS-00
U.S.
7-17
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FLIGHT INSTRUMENTS (Continued)
AIRSPEED INDICATOR
The G1000 vertical tape airspeed indicator is shown along the upper
left side of the PFD. The airspeed indication data is provided by the air
data computer unit. Colored bands are provided to indicate the
maximum speed, high cruise speed caution range, normal operating
range, full wing flap operating range and low airspeed awareness band.
Calculated true airspeed is displayed in a window at the bottom edge of
the airspeed tape.
The standby (pneumatic) airspeed indicator is found on the lower
center instrument panel. Colored arcs are provided to indicate the
maximum speed, high cruise speed caution range, normal operating
range, full wing flap operating range and low airspeed awareness band.
ALTIMETER
The primary altitude indicator (altimeter) is found along the right side of
the attitude indicator on the PFD. The altitude indication data is
provided by the air data computer unit. The local barometric pressure is
set using the BARO knob on the GDU displays.
A cyan selectable altitude reference pointer, bug, is displayed on the
altimeter tape and is set using the ALT SEL knob on the GDU displays.
The altitude bug set-point is shown in a window at the top edge of the
altimeter.
The standby (aneroid) sensitive altimeter is found on the lower center
instrument panel.
(Continued Next Page)
7-18
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
FLIGHT INSTRUMENTS (Continued)
HORIZONTAL SITUATION INDICATOR
The Horizontal Situation Indicator (HSI) is found along the lower center
area of the PFD. The heading indication data is provided by the AHRS
and magnetometer units. The HSI combines a stabilized magnetic
direction indicator (compass card) with selectable navigation deviation
indicators for GPS or VHF navigation. The HSI is conventional in
appearance and operation.
Magnetic heading is shown numerically in a window centered above
the heading index (lubber line) at the top of the HSI. Reference index
marks are provided at 45° intervals around the compass card. A
circular segment scale below the heading window at the top of the HSI
shows half and standard rates of turn based on the length of the
magenta turn vector.
The cyan HSI heading reference pointer, bug, is set using the HDG
knob on the GDU display. The selected heading is shown digitally in a
window above the upper left 45° index mark. The selected heading will
provide control input to the autopilot, if installed, when engaged in HDG
mode.
The CDI navigation source shown on the HSI is set using the CDI
softkey to select from GPS, NAV 1 or NAV 2 inputs. The course
reference pointer is set using the CRS knob on the GDU display. The
selected course is shown digitally in a window above the upper right
45° index mark. The selected navigation source will provide control
input to the autopilot, if installed, when engaged in NAV, APR or BC
mode and it is receiving a navigation signal from the selected GPS or
VHF NAV radios.
(Continued Next Page)
172RPHBUS-00
U.S.
7-19
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FLIGHT INSTRUMENTS (Continued)
HORIZONTAL SITUATION INDICATOR (Continued)
WARNING
WHEN THE AUTOPILOT IS ENGAGED IN NAV, APR OR
BC OPERATING MODES, IF THE HSI NAVIGATION
SOURCE IS CHANGED MANUALLY, USING THE CDI
SOFTKEY, THE CHANGE WILL INTERRUPT THE
NAVIGATION SIGNAL TO THE AUTOPILOT AND WILL
CAUSE THE AUTOPILOT TO REVERT TO ROL MODE
OPERATION. NO AURAL ALERT WILL BE PROVIDED.
IN ROL MODE, THE AUTOPILOT WILL ONLY KEEP THE
WINGS LEVEL AND WILL NOT CORRECT THE
AIRPLANE HEADING OR COURSE. SET THE HDG BUG
TO THE CORRECT HEADING AND SELECT THE
CORRECT NAVIGATION SOURCE ON THE HSI, USING
THE CDI SOFTKEY, BEFORE ENGAGING THE
AUTOPILOT IN ANY OTHER OPERATING MODE.
VERTICAL SPEED INDICATOR
The Vertical Speed Indicator (VSI) tape is found on the right side of the
altimeter display along the upper right side of the PFD. The vertical
speed pointer moves up and down the fixed VSI scale and shows the
rate of climb or descent in digits inside the pointer. The VSI tape has a
notch on the right edge at the 0 feet/min index for reference. Rate of
descent is shown with a negative sign in front of the digits. Vertical
speed must exceed 100 feet/min in climb or descent before digits will
appear in the VSI pointer.
7-20
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
GROUND CONTROL
Effective ground control while taxiing is accomplished through
nosewheel steering by using the rudder pedals; left rudder pedal to
steer left and right rudder pedal to steer right. When a rudder pedal is
depressed, a spring loaded steering bungee, which is connected to the
nose gear and to the rudder bars, will turn the nosewheel through an
arc of approximately 10° each side of center. By applying either left or
right brake, the degree of turn may be increased up to 30° each side of
center.
Moving the airplane by hand is most easily accomplished by attaching
a towbar to the nose gear strut. If a towbar is not available, or pushing
is required, use the wing struts as push points. Do not use the vertical
or horizontal surfaces to move the airplane. If the airplane is to be
towed by vehicle, never turn the nosewheel more than 30° either side
of center or structural damage to the nose gear could result.
The minimum turning radius of the airplane, using differential braking
and nosewheel steering during taxi, is approximately 27 feet. To obtain
a minimum radius turn during ground handling, the airplane may be
rotated around either main landing gear by pressing down on a tailcone
bulkhead just forward of the horizontal stabilizer to raise the nosewheel
off the ground. Care should be exercised to ensure that pressure is
exerted only on the bulkhead area and not on skin between the
bulkheads. Pressing down on the horizontal stabilizer to raise the
nosewheel off the ground is not recommended.
172RPHBUS-00
U.S.
7-21
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
WING FLAP SYSTEM
The single slot type wing flaps, Refer to Figure 7-3, are extended or
retracted by positioning the wing flap control lever on the instrument
panel to the desired flap deflection position. The wing flap control lever
is moved up or down in a slotted panel that provides mechanical stops
at the 10°, 20° and FULL positions. To change flap setting, the wing flap
control lever is moved to the right to clear mechanical stops at the 10°
and 20° positions. A scale and pointer to the left of the wing flap control
lever indicates flap travel in degrees. The wing flap system circuit is
protected by a 10-ampere circuit breaker, labeled FLAP, on the left side
of the circuit breaker panel.
Figure 7-3
7-22
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
LANDING GEAR SYSTEM
The landing gear is of the tricycle type, with a steerable nosewheel and
two main wheels. Wheel fairings are standard equipment for both the
main wheels and nosewheel. Shock absorption is provided by the
tubular spring steel main landing gear struts and the air/oil nose gear
shock strut. Each main gear wheel is equipped with a hydraulicallyactuated disc type brake on the inboard side of each wheel.
BAGGAGE COMPARTMENT
The baggage compartment consists of two areas, one extending from
behind the rear passengers seat to the aft cabin bulkhead, and an
additional area aft of the bulkhead. Access to both baggage areas is
gained through a lockable baggage door on the left side of the airplane,
or from within the airplane cabin. A baggage net with tiedown straps is
provided for securing baggage and is attached by tying the straps to
tiedown rings provided in the airplane. For baggage area and door
dimensions, refer to Section 6.
172RPHBUS-00
U.S.
7-23
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SEATS
The seating arrangement consists of two vertically adjusting crew seats
for the pilot and front seat passenger, and a single bench seat with
adjustable back for rear seat passengers.
Seats used for the pilot and front seat passenger are adjustable
forward and aft, and up and down. Additionally, the angle of the seat
back is infinitely adjustable.
Forward and aft adjustment is made using the handle located below the
center of the seat frame. To position the seat, lift the handle, slide the
seat into position, release the handle and check that the seat is locked
in place. To adjust the height of the seat, rotate the large crank under
the right corner of the seat until a comfortable height is obtained. To
adjust the seat back angle, pull up on the release button, located in
center front of seat, just under the seat bottom, position the seat back
to the desired angle, and release the button. When the seat is not
occupied, the seat back will automatically fold forward whenever the
release button is pulled up.
The rear passenger seat consists of a fixed, one piece seat bottom and
a three-position reclining back. The reclining back is adjusted by a lever
located below the center of the seat frame. To adjust the seat back,
raise the lever, position the seat back to the desired angle, release the
lever, and check that the seat back is securely locked in place.
Headrests are installed on both the front and rear seats. To adjust the
headrest, apply enough pressure to it to raise or lower it to the desired
level.
7-24
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
INTEGRATED SEAT BELT/SHOULDER HARNESS
All seat positions are equipped with integrated seat belts/shoulder
harness assemblies, Refer to Figure 7-4. The design incorporates an
overhead inertia reel for the shoulder portion, and a retractor assembly
for the lap portion of the belt. This design allows for complete freedom
of movement of the upper torso area while providing restraint in the lap
belt area. In the event of a sudden deceleration, reels lock up to provide
positive restraint for the user.
In the front seats, the inertia reels are located on the centerline of the
upper cabin area. In the rear seats, the inertia reels are located
outboard of each passenger in the upper cabin.
To use the integrated seat belt/shoulder harness, grasp the link with
one hand, and, in a single motion, extend the assembly and insert into
the buckle. Positive locking has occurred when a distinctive “snap”
sound is heard.
Proper locking of the lap belt can be verified by ensuring that the belts
are allowed to retract into the retractors and the lap belt is snug and low
on the waist as worn normally during flight. No more than one
additional inch of belt should be able to be pulled out of the retractor
once the lap belt is in place on the occupant. If more than one
additional inch of belt can be pulled out of the retractor, the occupant is
too small for the installed restraint system and the seat should not be
occupied until the occupant is properly restrained.
Removal is accomplished by pressing the release button on the buckle
and pulling out and up on the harness. Spring tension on the inertia reel
will automatically stow the harness.
172RPHBUS-00
U.S.
7-25
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
INTEGRATED SEAT BELT/SHOULDER HARNESS
Figure 7-4
7-26
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ENTRANCE DOORS AND CABIN WINDOWS
Entry to and exit from the airplane is accomplished through either of
two entry doors, one on each side of the cabin, at the front seat
positions, Refer to Section 6 for cabin and cabin door dimensions. The
doors incorporate a recessed exterior door handle, a conventional
interior door handle, a key operated door lock, left door only, a door
stop mechanism, and openable windows in both the left and right
doors.
NOTE
The door latch design on this model requires that the
outside door handle on the pilot and front passenger doors
be extended out whenever the doors are open. When
closing the door, do not attempt to push the door handle in
until the door is fully shut.
To open the doors from outside the airplane, utilize the recessed door
handle near the aft edge of either door by grasping the forward edge of
the handle and pulling outboard. To close or open the doors from inside
the airplane, use the combination door handle and arm rest. The inside
door handle has three positions and a placard at its base which reads
OPEN, CLOSE, and LOCK. The handle is spring loaded to the CLOSE
(up) position. When the door has been pulled shut and latched, lock it
by rotating the door handle forward to the LOCK position (flush with the
arm rest). When the handle is rotated to the LOCK position, an over
center action will hold it in that position. Both cabin doors should be
locked prior to flight, and should not be opened intentionally during
flight.
NOTE
Accidental opening of a cabin door in flight, due to improper
closing, does not constitute a need to land the airplane. The
best procedure is to set up the airplane in a trimmed
condition at approximately 75 KIAS, momentarily shove the
door outward slightly, and forcefully close and lock the door.
(Continued Next Page)
172RPHBUS-00
U.S.
7-27
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ENTRANCE DOORS AND CABIN WINDOWS
(Continued)
Exit from the airplane is accomplished by rotating the door handle from
the LOCK position, past the CLOSE position, aft to the OPEN position
and pushing the door open. To lock the airplane, lock the right cabin
door with the inside handle, close the left cabin door, and using the
ignition key, lock the door.
The left and right cabin doors are equipped with openable windows
which are held in the closed position by a detent equipped latch on the
lower edge of the window frame. To open the windows, rotate the latch
upward. Each window is equipped with a spring-loaded retaining arm
which will help rotate the window outward, and hold it there. If required,
either window may be opened at any speed up to 163 KIAS. The rear
side windows and rear windows are of the fixed type and cannot be
opened.
CONTROL LOCKS
A control lock is provided to lock the aileron and elevator control
surfaces to prevent damage to these systems by wind buffeting while
the airplane is parked. The lock consists of a shaped steel rod and flag.
The flag identifies the control lock and cautions about its removal
before starting the engine. To install the control lock, align the hole in
the top of the pilot’s control wheel shaft with the hole in the top of the
shaft collar on the instrument panel and insert the rod into the aligned
holes. Installation of the lock will secure the ailerons in a neutral
position and the elevators in a slightly trailing edge down position.
Proper installation of the lock will place the flag over the ignition switch.
In areas where high or gusty winds occur, a control surface lock should
be installed over the vertical stabilizer and rudder. The control lock and
any other type of locking device should be removed prior to starting the
engine.
7-28
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ENGINE
The airplane is powered by a direct drive, horizontally opposed, four
cylinder, overhead valve, air cooled, fuel injected engine with a wet
sump lubrication system. The engine is a Lycoming Model IO-360-L2A
rated at 160 horsepower at 2400 RPM. Major accessories include a
starter and belt driven alternator mounted on the front of the engine,
dual magnetos, vacuum pump, engine driven fuel pump, and a full flow
oil filter mounted on the rear of the engine accessory case.
ENGINE CONTROLS
Engine power is set using the throttle control. The throttle control is a
smooth black knob located at the center of the instrument panel below
the standby instruments. The throttle control is configured so that the
throttle is open in the forward position and closed in the full aft position.
A friction lock, located at the base of the throttle, is operated by rotating
the lock clockwise to increase friction or counterclockwise to decrease
friction.
Engine fuel mixture is controlled by the mixture control. The mixture
control is a red knob, with raised points around the circumference,
located immediately to the right of the throttle control and is equipped
with a lock button in the end of the knob. The rich position is full
forward, and full aft is the idle cutoff position. For small adjustments, the
control may be moved forward by rotating the knob clockwise, and aft
by rotating the knob counterclockwise. For rapid or large adjustments,
the knob may be moved forward or aft by depressing the lock button in
the end of the control, and then positioning the control as desired.
(Continued Next Page)
172RPHBUS-00
U.S.
7-29
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ENGINE (Continued)
ENGINE INSTRUMENTS
The G1000 Engine Indication System (EIS) provides graphical
indicators and numeric values for engine, fuel, and electrical system
parameters to the pilot. The EIS is shown in a vertical strip on the left
side of the PFD during engine starts and on the MFD during normal
operation. If either the MFD or PFD fails during flight, the EIS is shown
on the remaining display.
The EIS consists of three pages that are selected using the ENGINE
softkey. The ENGINE page provides indicators for Tachometer (RPM),
Fuel Flow (FFLOW GPH), Oil Pressure (OIL PRES), Oil Temperature
(OIL TEMP), Exhaust Gas Temperature (EGT), Vacuum (VAC), Fuel
Quantity (FUEL QTY GAL), Engine Hours (ENG HRS), Electrical Bus
Voltages (VOLTS), and Battery Currents (AMPS). When the ENGINE
softkey is pressed, the LEAN and SYSTEM softkeys appear adjacent to
the ENGINE softkey. The LEAN page provides simultaneous indicators
for Exhaust Gas Temperature (EGT °F) and Cylinder Head
Temperature (CHT °F) on all cylinders to be used for adjusting, or
leaning, the fuel/air mixture along with a digital value for FFLOW GPH
and a indicator for FUEL QTY GAL. The SYSTEM page provides
numerical values for parameters on the ENGINE page that are shown
as indicators only. The SYSTEM page also provides a digital value for
Fuel Used (GAL USED) and Fuel Remaining (GAL REM).
The engine and airframe unit, located forward of the instrument panel,
receives signals from the engine/system sensors for the parameters
that are being monitored. The engine and airframe unit provides data to
the EIS, which displays the data for the ENGINE page described on the
following pages.
(Continued Next Page)
7-30
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ENGINE (Continued)
ENGINE INSTRUMENTS (Continued)
RPM (TACHOMETER)
Engine speed (RPM) is shown by the tachometer indicator found on all
EIS pages. The tachometer indicator uses a circular scale with moving
pointer and a digital value. The pointer moves through a range from 0
to 2700 RPM. The numerical RPM value is displayed in increments of
10 RPM in white numerals below the pointer.
The normal engine speed operating limit (top of green arc) is 2400
RPM. When engine speed is 2472 RPM or more, the pointer, digital
value, and label (RPM) turn red to show engine speed is more than the
limit. The digital value and label (RPM) will flash. The engine speed
(tachometer) is displayed in the same configuration and location on the
LEAN and SYSTEM pages. If engine speed becomes 2472 RPM or
more, while on the LEAN or SYSTEM page, the display will return to
the ENGINE page.
A speed sensor, mounted on the engine tachometer drive accessory
pad, provides a digital signal to the engine and airframe unit which
processes and outputs the RPM data to the EIS. A red X through the
RPM indicator shows the indicating system is inoperative.
(Continued Next Page)
172RPHBUS-00
U.S.
7-31
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ENGINE (Continued)
ENGINE INSTRUMENTS (Continued)
FUEL FLOW
Fuel flow is shown on the ENGINE page by the FFLOW GPH horizontal
indicator. The indicator range is from 0 to 20 gallons per hour (GPH)
with 2 GPH graduations, with a green band from 0 to 11 GPH. A white
pointer shows the measured fuel flow.
A digital value for FFLOW GPH is included on both the EIS LEAN and
SYSTEM pages.
The fuel flow transducer is located in the engine fuel injection system
between the fuel/air control unit (servo) and the fuel distribution
manifold (flow divider). The transducer provides a signal to the engine
display that is processed and shown as fuel flow (FFLOW) on the EIS
pages. A red X through the indicator means the indicating system is
inoperative.
OIL PRESSURE
Engine oil pressure is shown on the ENGINE page by the OIL PRES
horizontal indicator. The indicator range is 0 to 120 PSI with a red band
from 0 to 20 PSI, a green band from 50 to 90 PSI (normal operating
range) and a red band from 115 to 120 PSI. A white pointer indicates
actual oil pressure. Oil pressure is shown numerically on the SYSTEM
page.
When oil pressure is 0 to 20 PSI or 115 to 120 PSI, the pointer, digital
value, and label (OIL PRES) will change to red to show that oil pressure
is outside normal limits. If oil pressure exceeds either the upper or
lower limit while on the LEAN or SYSTEM page, the EIS will return to
the ENGINE page.
When the engine speed (RPM) is in the green arc and the oil
temperature is in the green band, the oil pressure should be in the
green band. If oil pressure is below the green band or above the green
band, adjust the engine speed to maintain adequate oil pressure. When
engine speed is at idle or near idle, the oil pressure indication must be
above the lower red band. With the engine at normal operating oil
temperature, and engine speed at or close to idle, oil pressure below
the green band, but above the lower red band, is acceptable.
(Continued Next Page)
7-32
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ENGINE (Continued)
ENGINE INSTRUMENTS (Continued)
OIL PRESSURE (Continued)
In cold weather, the oil pressure will initially be high (close to the upper
red band when the engine is started). As the engine and oil warm up,
the oil pressure will come down into the green band range.
The oil pressure transducer, connected to the engine forward oil
pressure port, provides a signal to the engine display that is processed
and shown as oil pressure. A separate low oil pressure switch causes
an OIL PRESSURE annunciation on the PFD when oil pressure is 0 to
20 PSI. A red X through the oil pressure indicator means that the
indicating system is inoperative.
OIL TEMPERATURE
Engine oil temperature is shown on the ENGINE page by the OIL
TEMP horizontal indicator. The indicator range is from 75°F to 250°F
with a green band (normal operating range) from 100°F to 245°F and a
red band from 245°F to 250°F. A white pointer indicates actual oil
temperature. Oil temperature is displayed numerically on the SYSTEM
page.
When oil temperature is in the red band, 245°F to 250°F, the pointer
and OIL TEMP turn red and flash to show oil temperature is higher than
the limit. If oil temperature becomes hotter than 245°F while on the
LEAN or SYSTEM page, the display will default to the ENGINE page.
The oil temperature sensor is installed in the engine oil filter adapter
and provides a signal to the engine display that is processed and
shown as oil temperature. A red X through the indicator shows that the
indicating system is inoperative.
(Continued Next Page)
172RPHBUS-00
U.S.
7-33
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ENGINE (Continued)
ENGINE INSTRUMENTS (Continued)
CYLINDER HEAD TEMPERATURE
Cylinder head temperature (CHT) for all four cylinders are shown on
the LEAN page. The cylinder with the hottest CHT is indicated by a
cyan bar graph. The indicator range is from 100°F to 500°F with a
normal operating range from 200°F to 500°F and a warning range (red
line) at 500°F. When the CHT is 500°F or hotter, the bar segments,
CHT label and °F digital value will change to red to show that the CHT
is greater than the limit.
A thermocouple is installed in each cylinder head and provides a signal
to the engine display that is processed and shown as CHT on the EIS
LEAN page. The LEAN page will show a red X over any cylinder that
has a probe or wiring failure.
EXHAUST GAS TEMPERATURE
Exhaust gas temperature (EGT) is shown on the ENGINE page by the
EGT horizontal indicator. The indicator range is from 1250°F to 1650°F
with graduations every 50°F. The white pointer indicates relative EGT
with the number of the hottest cylinder displayed inside the pointer. If a
cylinder EGT probe or wiring failure occurs for the hottest EGT, the next
hottest EGT will be displayed.
The EGT for all four cylinders is shown on the LEAN page of the EIS.
The hottest cylinder is indicated by the cyan bar graph. The EGT for a
particular cylinder may be shown by using the CYL SLCT softkey to
select the desired cylinder. Automatic indication of the hottest cylinder
will resume a short time after the CYL SLCT is last selected. The LEAN
page will show a red X over a cylinder that has a probe or wiring failure.
A thermocouple is installed in the exhaust pipe of each cylinder which
measures EGT and provides a signal to the engine display that is
processed and shown as EGT on the EIS LEAN page.
(Continued Next Page)
7-34
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ENGINE (Continued)
NEW ENGINE BREAK-IN AND OPERATION
The engine run-in was accomplished at the factory and is ready for the
full range of use. It is suggested that cruising be accomplished at 80%
power as much as practicable until a total of 50 hours has accumulated
or oil consumption has stabilized. This will ensure proper seating of the
piston rings.
ENGINE LUBRICATION SYSTEM
The engine utilizes a full pressure, wet sump type lubrication system
with aviation grade oil as the lubricant. The capacity of the engine
sump, located on the bottom of the engine, is eight quarts with one
additional quart contained in the engine oil filter. Oil is drawn from the
sump through a filter screen on the end of a pickup tube to the engine
driven oil pump. Oil from the pump passes through a full-flow oil filter, a
pressure relief valve at the rear of the right oil gallery, and a
thermostatically controlled remote oil cooler. Oil from the remote cooler
is then circulated to the left oil gallery. The engine parts are then
lubricated by oil from the galleries. After lubricating the engine, the oil
returns to the sump by gravity. The filter adapter in the full-flow filter is
equipped with a bypass valve which will cause lubricating oil to bypass
the filter in the event the filter becomes plugged, or the oil temperature
is extremely cold.
An oil dipstick/filler tube is located at the right rear of the engine case.
The oil dipstick/filler tube is accessed through a door located on the
right side of the engine cowling. The engine should not be operated on
less than five quarts of oil. To minimize loss of oil through the breather,
fill to eight quarts for normal flights of less than three hours. For
extended flight, fill to eight quarts (dipstick indication only). For engine
oil grade and specifications, refer to Section 8 of this POH.
(Continued Next Page)
172RPHBUS-00
U.S.
7-35
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ENGINE (Continued)
IGNITION AND STARTER SYSTEM
Engine ignition is provided by two engine driven magnetos, and two
spark plugs in each cylinder. The left magneto fires the upper left and
lower right spark plugs, and the right magneto fires the lower left and
upper right spark plugs. Normal operation is conducted with both
magnetos due to the more complete burning of the fuel/air mixture with
dual ignition.
Ignition and starter operation is controlled by a rotary-type switch
located on the left switch and control panel. The MAGNETOS switch is
labeled clockwise, OFF, R, L, BOTH, and START. The engine should
be operated on both magnetos (BOTH position) except for magneto
checks. The R and L positions are for checking purposes and
emergency use only. When the MAGNETOS switch is rotated to the
spring-loaded START position, with the MASTER switch in the ON
position, the starter contactor is closed and the starter, now energized,
will crank the engine. When the switch is released, it will automatically
return to the BOTH position.
AIR INDUCTION SYSTEM
The engine air induction system receives ram air through an intake on
the lower front portion of the engine cowling. The intake is covered by
an air filter which removes dust and other foreign matter from the
induction air. Airflow passing through the filter enters an air box, which
is equipped with a spring-loaded alternate air door. If the air induction
filter should become blocked, suction created by the engine will open
the door and draw unfiltered air from inside the lower cowl area. An
open alternate air door will result in an approximate 10% power loss at
full throttle. After passing through the air box, induction air enters a fuel/
air control unit under the engine, and is then ducted to the engine
cylinders through intake manifold tubes.
(Continued Next Page)
7-36
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ENGINE (Continued)
EXHAUST SYSTEM
Exhaust gas from each cylinder passes through a riser assembly to a
common muffler, located below the engine, and then overboard through
a single tailpipe. Outside air is supplied to a shroud constructed around
the outside of the muffler to form a heating chamber. The air heated by
the shroud is then supplied to the cabin.
FUEL INJECTION SYSTEM
The engine is equipped with a fuel injection system. The system is
comprised of an engine driven fuel pump, fuel/air control unit, fuel
manifold, fuel flow indicator, and air-bleed type injector nozzles.
Fuel is delivered by the engine driven fuel pump to the fuel/air control
unit. The fuel/air control unit correctly proportions the fuel flow to the
induction air flow. After passing through the control unit, induction air is
delivered to the cylinders through the intake manifold tubes and
metered fuel is delivered to a fuel manifold (flow divider). The fuel
manifold, through spring tension on a diaphragm and valve, evenly
distributes the fuel to an air-bleed type injector nozzle in the intake
valve chamber of each cylinder. A turbine-type fuel flow transducer
mounted between the fuel/air control unit and the fuel distribution unit
produces a digital signal that displays fuel flow on the EIS pages.
COOLING SYSTEM
Ram air for engine cooling enters through two intake openings in the
front of the engine cowling. The cooling air is directed from above the
engine, around the cylinders and other areas of the engine by baffling,
and then exits through an opening at the bottom aft edge of the engine
cowling.
A winterization kit is available for the airplane. Refer to Section 9,
Supplement 4 for description and operating information.
PROPELLER
The airplane is equipped with a two bladed, fixed pitch, one-piece
forged aluminum alloy propeller which is anodized to retard corrosion.
The propeller is 75 inches in diameter.
172RPHBUS-00
U.S.
7-37
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FUEL SYSTEM
The airplane fuel system, Refer to Figure 7-6, consists of two vented
integral fuel tanks (one tank in each wing), three-position selector
valve, fuel reservoir tank, electrically-driven auxiliary fuel pump, fuel
shutoff valve, and a fuel strainer. The engine-mounted portion of the
system consists of the engine driven fuel pump, a fuel/air control unit,
fuel flow transducer, a fuel distribution valve (flow divider) and fuel
injection nozzles.
WARNING
UNUSABLE FUEL LEVELS FOR THIS AIRPLANE WERE
DETERMINED IN ACCORDANCE WITH FEDERAL
AVIATION REGULATIONS. FAILURE TO OPERATE THE
AIRPLANE IN COMPLIANCE WITH FUEL LIMITATIONS
SPECIFIED IN SECTION 2 MAY FURTHER REDUCE THE
AMOUNT OF FUEL AVAILABLE IN FLIGHT.
FUEL QUANTITY DATA IN U.S. GALLONS
FUEL LEVEL
FUEL (QUANTITY TOTAL
TOTAL
TANKS EACH TANK) FUEL UNUSABLE
TOTAL USABLE
ALL FLIGHT
CONDITIONS
Two
Full (28.0)
56.0
3.0
53.0
Two
Reduced (17.5)
35.0
3.0
32.0
Figure 7-5
(Continued Next Page)
7-38
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
FUEL SYSTEM (Continued)
FUEL DISTRIBUTION
Fuel flows by gravity from the two wing tanks to a three-position fuel
selector valve, labeled BOTH, RIGHT and LEFT, and on to the fuel
reservoir tank. From the fuel reservoir tank, fuel flows through the
electrically-driven auxiliary fuel pump, through the fuel shutoff valve,
the fuel strainer, and to the engine-driven fuel pump. From the enginedriven fuel pump, fuel is delivered to the fuel/air control unit on the
bottom of the engine. The fuel/air control unit (fuel servo) meters fuel
flow in proportion to induction air flow. After passing through the control
unit, metered fuel goes to a fuel distribution valve (flow divider) located
on the top of the engine. From the fuel distribution valve, individual fuel
lines are routed to air bleed type injector nozzles located in the intake
chamber of each cylinder.
FUEL INDICATING SYSTEM
Fuel quantity is measured by two fuel quantity sensors, one in each fuel
tank, and is displayed on the EIS pages. The indicators are marked in
gallons of fuel (GAL). An empty tank is displayed on the fuel quantity
indicator (FUEL QTY GAL) as a red line on the far left of the indicator
scale, and the number 0. When an indicator shows an empty tank,
approximately 1.5 gallons of unusable fuel remain in the tank. The
indicators should not be relied upon for accurate readings during skids,
slips or unusual attitudes.
The fuel quantity indicator shows the fuel available in the tank up to the
limit of the sensor measurement range. At this level, additional fuel may
be added to completely fill the tank, but no additional movement of the
indicator will result. The limit for sensor measurement range is
approximately 24 gallons and is indicated by the maximum limit of the
green band. When the fuel level decreases below the maximum limit of
the fuel sensor, the fuel quantity indicator will display fuel quantity
measured in each tank. A visual check of each wing tank fuel level
must be performed prior to each flight. Compare the visual fuel level
and indicated fuel quantity to accurately estimate usable fuel.
(Continued Next Page)
172RPHBUS-00
U.S.
7-39
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FUEL SYSTEM (Continued)
FUEL INDICATING SYSTEM (Continued)
The fuel quantity indicators detect low fuel conditions and incorrect
sensor outputs. When fuel quantity is less than 5 gallons indicated (and
remains less than this level for more than 60 seconds), LOW FUEL L
(left) and/or LOW FUEL R (right) will be displayed in amber on the PFD
and a tone will sound. The fuel quantity indicator pointer(s) and
indicator label will change from white to steady amber. When fuel
quantity reaches the calibrated usable fuel empty level, the LOW FUEL
L and/or LOW FUEL R remain amber and the indicator pointer(s) and
label change to flashing red.
NOTE
Takeoff is not recommended if both fuel quantity indicator
pointers are in the yellow band range and/or amber LOW
FUEL L or LOW FUEL R annunciator is displayed on the
PFD.
In addition to low fuel annunciation, the warning logic is designed to
report failures with each sensor. If the system detects a failure, the
affected fuel indicator will display a red X. A red X through the top part
of the indicator indicates a failure associated with the left fuel tank. A
red X through the bottom part of the indicator indicates a failure
associated with the right fuel tank.
Fuel flow is measured by use of a turbine type transducer mounted on
top of the engine between the fuel/air control unit and the fuel
distribution unit. This flow meter produces a signal that is displayed as
the rate of fuel flow on the FFLOW GPH indicator on the EIS pages.
FFLOW GPH is shown as either a horizontal analog indicator or a
digital value, depending on the active EIS page.
(Continued Next Page)
7-40
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
FUEL SYSTEM (Continued)
FUEL CALCULATIONS
NOTE
Fuel calculations do not use the airplane’s fuel quantity
indicators and are calculated from the last time the fuel was
reset.
For fuel consumption information, a fuel used totalizer function is
provided on the EIS SYSTEM page as GAL USED. This digital
indicator shows total fuel used since last reset of the totalizer. To reset
the GAL USED, the EIS SYSTEM page must be active and the RST
USED softkey must be selected. GAL USED is calculated after reset
using information from the fuel flow transducer signal.
For fuel remaining information, a count down fuel totalizer function is
provided on the EIS SYSTEM page as GAL REM. This digital indicator
shows calculated fuel remaining since last GAL REM pilot adjustment.
To adjust GAL REM, the EIS SYSTEM page must be active and the
GAL REM softkey must be selected followed by the appropriate
quantity adjustment softkeys. Refer to the Garmin G1000 CRG for
details for resetting and adjusting fuel calculations. GAL REM is
calculated after pilot adjustment using information from the fuel flow
transducer signal.
NOTE
GAL USED and GAL REM provide no indication of the
actual amount of fuel remaining in each tank and should
only be used in conjunction with other fuel management
procedures to estimate total fuel remaining.
(Continued Next Page)
172RPHBUS-00
U.S.
7-41
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FUEL SYSTEM (Continued)
Figure 7-6
7-42
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
FUEL SYSTEM (Continued)
AUXILIARY FUEL PUMP OPERATION
The auxiliary fuel pump is used primarily for priming the engine before
starting. Priming is accomplished through the fuel injection system. The
engine may be flooded if the auxiliary FUEL PUMP switch is
accidentally placed in the ON position for prolonged periods, with
MASTER Switch ON and mixture rich, with the engine stopped.
The auxiliary fuel pump is also used for vapor suppression in hot
weather. Normally, momentary use will be sufficient for vapor
suppression; however, continuous operation is permissible if required.
Turning on the auxiliary fuel pump with a normally operating enginedriven fuel pump will result in only a very minor enrichment of the
mixture.
It is not necessary to operate the auxiliary fuel pump during normal
takeoff and landing, since gravity and the engine-driven fuel pump will
supply adequate fuel flow. In the event of failure of the engine-driven
fuel pump, use of the auxiliary fuel pump will provide sufficient fuel to
maintain flight at maximum continuous power.
Under hot day, high altitude conditions, or conditions during a climb that
are conducive to fuel vapor formation, it may be necessary to utilize the
auxiliary fuel pump to attain or stabilize the fuel flow required for the
type of climb being performed. In this case, turn the auxiliary fuel pump
on, and adjust the mixture to the desired fuel flow. If fluctuating fuel flow
(greater than 1 GPH) is observed during climb or cruise at high
altitudes on hot days, place the auxiliary fuel pump switch in the ON
position to clear the fuel system of vapor. The auxiliary fuel pump may
be operated continuously in cruise.
(Continued Next Page)
172RPHBUS-00
U.S.
7-43
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FUEL SYSTEM (Continued)
FUEL RETURN SYSTEM
A fuel return system was incorporated to improve engine operation
during extended idle operation in hot weather environments. The major
components of the system include an orifice fitting located in the top of
the fuel-air control unit (fuel servo), fuel return line, with check valve,
and a fuel reservoir tank. The fuel return system is designed to return a
metered amount of fuel/vapor back to the fuel reservoir tank. The
increased fuel flow, due to the fuel return system, results in lower fuel
operating temperatures at the engine inlet, which minimizes the amount
of fuel vapor generated in the fuel lines during hot weather operations.
Refer to Section 4 for Hot Weather operating information.
FUEL VENTING
Fuel system venting is essential to system operation. Complete
blockage of the fuel venting system will result in decreasing fuel flow
and eventual engine stoppage. The fuel venting system consists of an
interconnecting vent line between the fuel tanks and a check valve
equipped overboard vent in the left fuel tank assembly. The overboard
vent protrudes from the bottom surface of the left wing, just inboard of
the wing strut upper attachment point. The fuel filler caps are vacuum
vented; the fuel filler cap vents will open and allow air to enter the fuel
tanks in case the overboard vents become blocked.
REDUCED TANK CAPACITY
The airplane may be serviced to a reduced capacity to permit heavier
cabin loadings. This is accomplished by filling each tank to the bottom
edge of the fuel filler indicator tab, thus giving a reduced fuel load of
17.5 gallons usable in each tank.
(Continued Next Page)
7-44
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
FUEL SYSTEM (Continued)
FUEL SELECTOR VALVE
The fuel selector is a three-position selector valve, labeled BOTH,
RIGHT and LEFT. The fuel selector valve should be in the BOTH
position for takeoff, climb, landing, and maneuvers that involve
prolonged slips or skids of more than 30 seconds. Operation on either
LEFT or RIGHT fuel tank is reserved for level cruising flight only.
NOTE
•
When the fuel selector valve is placed in the BOTH
position, while in cruise flight, unequal fuel flow from
each tank may occur if the wings are not maintained
exactly level. Unequal fuel flow can be detected by one
fuel tank indicating more fuel than the other on the L
FUEL and R FUEL indicators. The resulting fuel
imbalance can be corrected by turning the fuel selector
valve to the fuel tank indicating the highest fuel quantity.
O n c e t h e L F U E L a n d R F U E L i n di c at o r s ha v e
equalized, position the fuel selector valve to the BOTH
position.
•
It is not practical to measure the time required to
consume all of the fuel in one tank, and, after switching
to the opposite tank, expect an equal duration from the
remaining fuel. The airspace in both fuel tanks is
interconnected by a vent line and, therefore, some
sloshing of fuel between tanks can be expected when
the tanks are nearly full and the wings are not level.
•
When the fuel tanks are 1/4 tank or less, prolonged
uncoordinated flight, such as slips or skids, can uncover
the fuel tank outlets causing fuel starvation and engine
stoppage. Therefore, if operating with one fuel tank dry
or operating on either LEFT or RIGHT tank with 1/4 tank
or less, do not allow the airplane to remain in
uncoordinated flight for periods in excess of 30 seconds.
(Continued Next Page)
172RPHBUS-00
U.S.
7-45
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FUEL SYSTEM (Continued)
FUEL DRAIN VALVES
The fuel system is equipped with drain valves to provide a means for
the examination of fuel in the system for contamination and grade. The
system should be examined before each flight and after each refueling,
by using the sampler cup provided to drain fuel from each wing tank
sump, the fuel reservoir tank sump, the fuel selector valve drain and the
fuel strainer sump. If any evidence of fuel contamination is found, it
must be eliminated in accordance with the preflight inspection checklist
and the discussion in Section 8. If takeoff weight limitations for the next
flight permit, the fuel tanks should be filled after each flight to prevent
condensation.
BRAKE SYSTEM
The airplane has a single-disc, hydraulically-actuated brake on each
main landing gear wheel. Each brake is connected, by a hydraulic line,
to a master cylinder attached to each of the pilot's rudder pedals. The
brakes are operated by applying pressure to the top of either the left
(pilot's) or right (copilot's) set of rudder pedals, which are
interconnected. When the airplane is parked, both main wheel brakes
may be set by utilizing the parking brake which is operated by a handle
under the left side of the instrument panel. To apply the parking brake,
set the brakes with the rudder pedals, pull the handle aft, and rotate it
90° down.
For maximum brake life, keep the brake system properly maintained,
and minimize brake usage during taxi operations and landings.
Some of the symptoms of impending brake failure are: gradual
decrease in braking action after brake application, noisy or dragging
brakes, soft or spongy pedals, and excessive travel and weak braking
action. If any of these symptoms appear, the brake system is in need of
immediate attention. If, during taxi or landing roll, braking action
decreases, let up on the pedals and then reapply the brakes with heavy
pressure. If the brakes become spongy or pedal travel increases,
pumping the pedals should build braking pressure. If one brake
becomes weak or fails, use the other brake sparingly while using
opposite rudder, as required, to offset the good brake
7-46
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ELECTRICAL SYSTEM
The airplane is equipped with a 28-volt direct current (DC) electrical
system, Refer to Figure 7-7. A belt-driven 60 ampere alternator powers
the system. A 24-volt main storage battery is located inside the engine
cowling on the left firewall. The alternator and main battery are
controlled through the MASTER switch found near the top of the pilot's
switch panel.
Power is supplied to most electrical circuits through two primary buses
(ELECTRICAL BUS 1 and ELECTRICAL BUS 2), with an essential bus
and a crossfeed bus connected between the two primary buses to
support essential equipment.
The system is equipped with a secondary or standby battery located
between the firewall and the instrument panel. The STBY BATT switch
controls power to or from the standby battery. The standby battery is
available to supply power to the essential bus in the event that
alternator and main battery power sources have both failed.
The primary buses are supplied with power whenever the MASTER
switch is turned on, and are not affected by starter or external power
usage. Each primary bus is also connected to an avionics bus through
a circuit breaker and the AVIONICS BUS 1 and BUS 2 switches. Each
avionics bus is powered when the MASTER switch and the
corresponding AVIONICS switch are in the ON position.
CAUTION
B O T H B U S 1 A N D B U S 2 AV I O N I C S S W I T C H E S
SHOULD BE TURNED OFF TO PREVENT ANY
HARMFUL TRANSIENT VOLTAGE FROM DAMAGING
THE AVIONICS EQUIPMENT PRIOR TO TURNING THE
MASTER SWITCH ON OR OFF, STARTING THE ENGINE
OR APPLYING AN EXTERNAL POWER SOURCE.
The airplane includes a power distribution module, located on the left
forward side of the firewall, to house all the relays used in the airplane
electrical system. The Alternator Control Unit (ACU), main battery
current sensor, and the external power connector are also housed
within the module.
(Continued Next Page)
172RPHBUS-00
U.S.
7-47
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ELECTRICAL SYSTEM (Continued)
Figure 7-7 (Sheet 1 of 3)
7-48
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ELECTRICAL SYSTEM (Continued)
Figure 7-7 (Sheet 2)
172RPHBUS-00
U.S.
7-49
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ELECTRICAL SYSTEM (Continued)
Figure 7-7 (Sheet 3)
7-50
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ELECTRICAL SYSTEM (Continued)
G1000 ANNUNCIATOR PANEL
All system alerts, cautions and warnings are shown on the right side of
the PFD screen adjacent to the vertical speed indicator. The following
annunciations are supported:
OIL PRESSURE
LOW FUEL L
LOW VOLTS
STBY BATT
LOW VACUUM
LOW FUEL R
HIGH VOLTS
CO LVL HIGH
Refer to the Garmin G1000 CRG Appendix A for more information on
system annunciations.
MASTER SWITCH
The MASTER switch is a two-pole, rocker-type switch. The BAT side of
the switch controls the main battery electrical power to the airplane.
The ALT side of the switch controls the alternator system.
In normal operation, both sides of the switch (ALT and BAT) are ON
simultaneously; however, the BAT side of the switch may be selected
separately as necessary. The ALT side of the switch can not be set to
ON without the BAT side of the switch also being set to ON.
If the alternator system fails, the MASTER switch may be set in the
OFF position to preserve main battery capacity for later in the flight.
With the MASTER switch OFF and the STBY BATT switch in the ARM
position, the standby battery will power the essential bus for a limited
time. Time remaining may be estimated by monitoring essential bus
voltage. At 20 Volts, the standby battery has little or no capacity
remaining.
(Continued Next Page)
172RPHBUS-00
U.S.
7-51
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ELECTRICAL SYSTEM (Continued)
STANDBY BATTERY SWITCH
The STBY BATT master switch is a three position (ARM-OFF-TEST)
switch that tests and controls the standby battery system. The energy
level of the battery shall be checked before starting the engine, Refer to
Section 4, by placing the switch in the momentary TEST position and
observing the correct illumination of the TEST lamp found to the right of
the switch. Energy level tests after starting engine are not
recommended.
Placing the switch in the ARM position during the engine start cycle
allows the standby battery to help regulate and filter essential bus
voltage during the start cycle. The switch is set to the ARM position
during normal flight operation to allow the standby battery to charge
and to be ready to power the essential bus in the event of alternator
and main battery failure. Placing the switch in the OFF position
disconnects the standby battery from the essential bus. Operation with
the STBY BATT switch in the OFF position prevents the standby battery
from charging and from automatically providing power should an
electrical system failure occur.
AVIONICS SWITCH
The AVIONICS switch is a two-pole rocker-type switch that controls
electrical power to AVIONICS BUS 1 and BUS 2. Placing either side of
the rocker switch in the ON position supplies power to the
corresponding avionics bus. Both sides of the AVIONICS switch should
be placed in the OFF position before turning the MASTER switch ON or
OFF, starting the engine, or applying an external power source.
(Continued Next Page)
7-52
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ELECTRICAL SYSTEM (Continued)
ELECTRICAL
SYSTEM
ANNUNCIATIONS
MONITORING
AND
BUS VOLTAGE (VOLTMETERS)
Voltage indication (VOLTS) for the main and essential buses is
provided at the bottom of the EIS bar (along the left margin of the MFD
or PFD), labeled M BUS E. Main bus voltage is shown numerically
below the M. Essential bus voltage is displayed numerically below the
E. The main bus voltage is measured at the WARN circuit breaker on
the crossfeed bus. The essential bus voltage is measured at the NAV1
ENG circuit breaker on the essential bus.
Normal bus voltages with the alternator operating shall be about 28.0
volts. When the voltage for either main or essential buses is above 32.0
volts, the numerical value and VOLTS text turns red. This warning
indication, along with the HIGH VOLTS annunciation, is an indication
that the alternator is supplying too high of a voltage. The ALT MASTER
Switch should immediately be positioned to OFF (Refer to Section 3,
Emergency Procedures, HIGH VOLTS ANNUNCIATOR COMES ON).
When the voltage for either main or essential buses is below 24.5 volts,
the numeric value and VOLTS text turns red. This warning indication,
along with the LOW VOLTS annunciation, is an indication that the
alternator is not supplying all the power that is required by the airplane.
Indicated voltages between 24.5 and 28.0 volts may occur during low
engine RPM conditions (Refer to note under LOW VOLTAGE
ANNUNCIATION).
(Continued Next Page)
172RPHBUS-00
U.S.
7-53
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ELECTRICAL SYSTEM (Continued)
ELECTRICAL
SYSTEM
ANNUNCIATIONS (Continued)
MONITORING
AND
AMMETERS
Current indication (AMPS) for both the main and standby batteries is
provided at the bottom of the EIS bar (along the left margin of the MFD
or PFD), labeled M BATT S. Main battery current is numerically
displayed below the M. Main battery current greater than -1.5 amps is
shown in white. Standby battery current is displayed numerically below
the S. A positive current value (shown in white) indicates that the
battery is charging. A negative current value (shown in amber)
indicates that the battery is discharging. In the event the alternator is
not functioning or the electrical load exceeds the output of the
alternator, the main battery ammeter indicates the main battery
discharge rate.
In the event that standby battery discharge is required, normal steady
state discharge should be less than 4.0 amps. The STBY BATT
annunciator will come on when discharge rates are greater than 0.5
amps for more than 10 seconds. After engine start, with the STBY
BATT switch in the ARM position, the standby battery ammeter should
indicate a charge showing correct charging of the standby battery
system.
STANDBY BATTERY ANNUNCIATION
The STBY BATT annunciator will come on when discharge rates are
greater then 0.5 amps for more than 10 seconds. This caution
annunciation is an indication that the alternator and the main battery
are not supplying the power that is required by the essential bus. If the
condition causing the caution can not be resolved, flight should be
terminated as soon as practicable.
(Continued Next Page)
7-54
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ELECTRICAL SYSTEM (Continued)
ELECTRICAL
SYSTEM
ANNUNCIATIONS (Continued)
MONITORING
AND
LOW VOLTAGE ANNUNCIATION
A signal from the ACU, located inside the power distribution module,
provides the trigger for a red LOW VOLTS annunciation shown on the
PFD. LOW VOLTS is displayed when the main bus voltage measured
in the power distribution module is below 24.5 volts. The LOW VOLTS
warning annunciation is an indication that the alternator is not supplying
the power that is required by the airplane. If the conditions causing the
LOW VOLTS warning can not be resolved, nonessential electrical loads
should be eliminated and the flight should be terminated as soon as
practicable.
NOTE
During low RPM operation, with a high electrical load on the
system, such as during a low RPM taxi, the LOW VOLTS
annunciation may come on, the bus voltage values may
turn red, and main battery ammeter discharge indications
may occur. Under these conditions, increase RPM or
decrease electrical loads to reduce demand on the battery.
In the event an overvoltage condition (or other alternator fault) occurs,
the ACU will automatically open the ALT FIELD circuit breaker,
removing alternator field current and stopping alternator output. The
main battery will then supply current to the electrical system as shown
by a discharge (negative number) on the M BATT ammeter. The LOW
VOLTS annunciator will come on when the system voltage drops below
24.5 volts. Set the ALT FIELD circuit breaker to the ON position (push
in) to energize the ACU. If the warning annunciation goes out and the
main battery (M BATT) ammeter indicates positive current, normal
alternator charging has resumed. If the annunciator comes on again, or
the ALT FIELD circuit breaker opens again, an alternator malfunction
has occurred. If the circuit breaker opens again, do not SET it to the ON
position again. Have a qualified technician determine the cause and
correct the malfunction. Turn off nonessential electrical loads and land
as soon as practicable.
(Continued Next Page)
172RPHBUS-00
U.S.
7-55
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ELECTRICAL SYSTEM (Continued)
ELECTRICAL
SYSTEM
ANNUNCIATIONS (Continued)
MONITORING
AND
LOW VOLTAGE ANNUNCIATION (Continued)
The ALT FIELD circuit breaker may open on occasion during normal
engine starts due to transient voltages. Provided that normal alternator
output is resumed after the ALT FIELD circuit breaker is reset, these
occurrences are considered nuisance events. If the ALT FIELD circuit
breaker opens after reset, do not close again. Repeated occurrences
indicate a problem with the electrical system that must be corrected by
a qualified maintenance technician before flight.
HIGH VOLTAGE ANNUNCIATION
The HIGH VOLTS annunciator will come on when main or essential bus
voltage is above 32.0 volts. This warning annunciation is an indication
that the alternator is supplying too high of a voltage. The ALT MASTER
switch should immediately be positioned to OFF (Refer to Section 3,
Emergency Procedures, HIGH VOLTS ANNUNCIATOR COMES ON).
In the event a HIGH VOLTS condition occurs, the ACU will
automatically open the ALT FIELD circuit breaker, removing alternator
field current and stopping alternator output. The HIGH VOLTS
annunciator is a warning that the ACU automatic alternator shutdown
circuit is not operational and an action from the pilot is required to
position the ALT MASTER to OFF.
(Continued Next Page)
7-56
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
ELECTRICAL SYSTEM (Continued)
CIRCUIT BREAKERS AND FUSES
Individual system circuit breakers are found on the circuit breaker panel
below the pilot's control wheel. All circuit breakers on ESSENTIAL
BUS, AVIONICS BUS 1 and AVIONICS BUS 2 are capable of being
opened, or disengaged from the electrical system, by pulling straight
out on the outer ring for emergency electrical load management. Using
a circuit breaker as a switch is discouraged since the practice will
decrease the life of the circuit breaker. All circuit breakers on
ELECTRICAL BUS 1, ELECTRICAL BUS 2 and CROSSFEED BUS
are not capable of being opened or disengaged.
The power distribution module uses three push-to-reset circuit breakers
for the electrical bus feeders. A fast blow automotive type fuse is used
at the standby battery. The standby battery current shunt circuit uses
two field replaceable fuses located on the standby battery controller
printed circuit board.
Most Garmin G1000 equipment has internal non-field replaceable
fuses. Equipment must be returned to Garmin by an approved service
station for replacement.
(Continued Next Page)
172RPHBUS-00
U.S.
7-57
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
ELECTRICAL SYSTEM (Continued)
EXTERNAL POWER RECEPTACLE
A external power receptacle is integral to the power distribution module
and allows the use of an external power source for cold weather
starting or for lengthy maintenance work on electrical and avionics
equipment. The receptacle is located on the left side of the cowl near
the firewall. Access to the receptacle is gained by opening the
receptacle door.
NOTE
Set the AVIONICS switches BUS 1 and BUS 2 to OFF if no
avionics are required. If maintenance on the avionics
equipment is required, a 28 VDC regulated and filtered
external power source must be provided to prevent damage
to the avionics equipment from transient voltages. Set
AVIONICS switches BUS 1 and BUS 2 to OFF before
starting the engine.
The following check should be made whenever the engine has been
started using external power (after disconnecting the external power
source).
1.
2.
3.
4.
MASTER Switch (ALT and BAT) - OFF
TAXI and LAND Light Switches - ON
Throttle Control - REDUCE TO IDLE
MASTER Switch (ALT and BAT) - ON (with taxi and landing lights
turned on)
5. Throttle Control - INCREASE (to approximately 1500 RPM)
6. Main Battery (M BATT) Ammeter - CHECK (Battery charging,
Amps Positive)
7. LOW VOLTS Annunciator - CHECK (Verify annunciator is not
shown)
WARNING
IF M BATT AMMETER DOES NOT SHOW POSITIVE
CHARGE (+ AMPS), OR LOW VOLTS ANNUNCIATOR
DOES NOT GO OFF, REMOVE THE BATTERY FROM
THE AIRPLANE AND SERVICE OR REPLACE THE
BATTERY BEFORE FLIGHT.
7-58
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
LIGHTING SYSTEMS
EXTERIOR LIGHTING
Exterior lighting consists of navigation lights on the wing tips and the tip
of the vertical stabilizer, landing/taxi lights located on the left wing
leading edge, a flashing beacon mounted on top of the vertical
stabilizer, and a strobe light on each wing tip.
Two courtesy lights are recessed into the lower surfaces of each wing
and provide illumination for each cabin door area. The switch for the
courtesy lights is found on the pilot's overhead console. The rear dome
light and under-wing courtesy lights share the same control switch.
Pressing the rear dome light switch will make the lights come on and
pressing it again will make the lights go out.
All other exterior lights are operated by switches found on the lighted
switch panel to the left of the PFD. Exterior lights are grouped together
in the LIGHTS section of the switch panel. To activate the BEACON,
LAND (landing light), TAXI (taxi light), NAV, and STROBE light(s), place
the switch in the up position. Circuit breakers for the lights are found on
the lighted circuit breaker panel on the lower left instrument panel,
below the PFD. Circuit breakers are grouped by electrical bus with
BEACON and LAND on ELECTRICAL BUS 1 and TAXI, NAV and
STROBE on ELECTRICAL BUS 2.
NOTE
The strobes and flashing beacon should not be used when
flying through clouds or overcast; the flashing light reflected
from water droplets or particles in the atmosphere,
particularly at night, can produce vertigo and loss of
orientation.
(Continued Next Page)
172RPHBUS-00
U.S.
7-59
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
LIGHTING SYSTEMS (Continued)
INTERIOR LIGHTING
Interior lighting is controlled by a combination of dimmable crew area
flood lighting, internally lit switch and circuit breaker panels, avionics
panel lighting, standby instrument lighting, pedestal lighting, pilot
control wheel map lighting and passenger area flood lighting.
Flood lighting is accomplished using two dimmable lights in the front
crew area and one dome light in the rear passenger area. These lights
are contained in the overhead console, and are controlled by dimmer
controls for the front flood lights, and an on-off type push button switch
for the rear dome light. The front flood lights can be rotated to provide
directional lighting for the pilot and front passenger. The rear dome light
provides for general illumination in the rear cabin area. Rear dome light
and courtesy lights, located under the wing, share the same control
switch.
Lighting of the switch panel, circuit breaker panel, engine controls and
environmental control panel is accomplished by using internally lit LED
panels. Rotating the SW/CB PANELS dimmer, found on the switch
panel in the DIMMING group, controls the lighting level for both panels.
Rotating the dimmer counterclockwise decreases light intensity from
the highest level to off.
Pedestal lighting consists of a LED strip light incorporated into the
Throttle/Flap Control Lever panel located on the bottom of the center
instrument panel and a second LED strip light incorporated into the
pedestal directly above the 12 volt cabin power outlet. Rotating the
PEDESTAL light dimmer, found on the switch panel in the DIMMING
group, controls the pedestal lights. Rotating the dimmer
counterclockwise decreases light intensity from the highest level to off.
(Continued Next Page)
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CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
LIGHTING SYSTEMS (Continued)
INTERIOR LIGHTING (Continued)
Avionics panel lighting consists of the PFD and MFD bezel and display
lighting and audio panel lighting. Rotating the AVIONICS dimmer, found
on the switch panel in the DIMMING group, controls the lighting level.
Positioning the dimmer control in the off position, rotated fully
counterclockwise, causes the avionics displays to use internal
photocells to automatically control the lighting levels. This is the
recommended use of the avionics lighting for all day and lower lighting
levels where lighting of the avionics bezels and keys is not required. In
low to night lighting levels rotating the AVIONICS dimmer control
clockwise from the off position places all avionics lighting level control
to the AVIONICS dimmer control. This is the recommended use of
avionics lighting for night and low lighting conditions to allow the pilot
control of the avionics illumination levels as dark adaptation occurs.
Rotating the STBY IND dimmer control, found on the switch panel in
the DIMMING group, controls lighting of the standby airspeed indicator,
attitude indicator, altimeter and non-stabilized magnetic compass.
Rotating the dimmer control counterclockwise decreases light intensity
from the highest level to off.
Pilot's chart (map) lighting is accomplished by use of a rheostat and a
light assembly, both found on the lower surface of the pilot's control
wheel. The light provides downward illumination from the bottom of the
control wheel to the pilot's lap area. To operate the light, first turn the
NAV light switch ON, and then adjust the map light intensity using the
knurled rheostat knob. Rotating the dimmer clockwise (when facing up)
increases light intensity, and rotating the dimmer counterclockwise
decreases light intensity.
Regardless of the light system in question, the most probable cause of
a light failure is a burned out bulb. However, in the event any lighting
systems fails to come on, check the appropriate circuit breaker. For
interior lighting failure check the PANEL LTS circuit breaker, and for
exterior lighting failure check the associated light function circuit
breaker (i.e. landing light, LAND LT circuit breaker). If the circuit
breaker has opened, and there is no obvious indication of a short circuit
(smoke or odor), turn the affected lights OFF, reset the circuit breaker,
and turn the lights ON again. If the circuit breaker opens again, do not
reset until maintenance has been performed.
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SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CABIN HEATING, VENTILATING AND DEFROSTING
SYSTEM
The temperature and volume of airflow into the cabin can be regulated
by manipulation of the push-pull CABIN HT and CABIN AIR control
knobs, Refer to Figure 7-8. Both control knobs are the double button
locking-type and permit intermediate control settings.
For cabin ventilation, pull the CABIN AIR control knob full out. To raise
the air temperature, pull the CABIN HT control knob out approximately
1/4 to 1/2 inch for a small amount of cabin heat. Additional heat is
available by pulling the CABIN HT control knob out farther; maximum
heat is available with the CABIN HT control knob pulled full out and the
CABIN AIR control knob pushed full in. When no heat is desired in the
cabin, the CABIN HT control knob is pushed full in.
Front cabin heat and ventilating air is supplied by outlet holes spaced
across a cabin manifold just forward of the pilot's and front passenger's
feet. Rear cabin heat and air is supplied by two ducts from the manifold,
one extending down each side of the cabin to an outlet just aft of the
rudder pedals at floor level. Windshield defrost air is also supplied by
two ducts leading from the cabin manifold to defroster outlets near the
lower edge of the windshield. Two knobs control sliding valves in either
defroster outlet to permit regulation of defroster airflow.
Separate adjustable ventilators supply additional air; one near each
upper corner of the windshield supplies air for the pilot and front
passenger, and two ventilators are available for the rear cabin area to
supply air to the rear seat passengers. There are additional ventilators
located in various positions in the cockpit.
7-62
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MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CABIN HEATING, VENTILATION AND DEFROSTING SYSTEM
Figure 7-8
172RPHBUS-00
U.S.
7-63
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
PITOT-STATIC SYSTEM AND INSTRUMENTS
The pitot-static system uses a heated total pressure (pitot) head
mounted on the lower surface of the left wing, external static port
mounted on the left side of the forward fuselage and associated
plumbing to connect the air data computer and the conventional pitotstatic instruments to the sources.
The heated pitot system uses an electrical heating element built in the
body of the pitot head. The PITOT HEAT control switch is found on the
switch panel below the lower left corner of the PFD. The PITOT HEAT
circuit breaker is found on the circuit breaker panel at the lower left side
of the pilot panel.
A static pressure alternate source valve (ALT STATIC AIR) is located
adjacent to the throttle control. The ALT STATIC AIR valve provides
static pressure from inside the cabin if the external static pressure
source becomes blocked.
If erroneous instrument readings are suspected due to water or ice in
the pressure line going to the standard external static pressure source,
the alternate static source valve should be pulled on.
Pressures within the cabin will vary with open heaters/vents and
windows. Refer to Section 5, Figure 5-1 (Sheet 2), for the Airspeed
Calibration, Alternate Static Source correction chart.
7-64
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172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
VACUUM SYSTEM AND INSTRUMENTS
The vacuum system, Refer to Figure 7-9, provides the vacuum
necessary to operate the standby attitude indicator. The system
consists of one engine-driven vacuum pump, a vacuum regulator, the
standby attitude indicator, a vacuum system air filter, and a vacuum
transducer. The vacuum transducer provides a signal to the engine
display that is processed and displayed as vacuum on the EIS ENGINE
page. If available vacuum, from the engine-driven vacuum pump, drops
below 3.5 in.hg., the LOW VACUUM annunciator will display in amber
on the PFD.
ATTITUDE INDICATOR
The standby attitude indicator is a vacuum-powered gyroscopic
instrument, found on the center instrument panel below the MFD. The
attitude indicator includes a low-vacuum warning flag (GYRO) that
comes into view when the vacuum is below the level necessary for
reliable gyroscope operation.
VACUUM INDICATOR
The vacuum indicator is incorporated on the EIS ENGINE page, found
along the left side of the PFD during engine start or the left edge of the
MFD during normal operation. During reversionary operation, the EIS
bar appears along the left side of the operational display.
LOW VACUUM ANNUNCIATION
A low vacuum condition is annunciated along the right side of the PFD
by a amber LOW VACUUM annunciator.
172RPHBUS-00
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7-65
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
VACUUM SYSTEM
Figure 7-9
7-66
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CLOCK/O.A.T. INDICATOR
A numerical time or clock window, based on GPS time, and an outside
air temperature (O.A.T.) indicator window are provided along the lower
edge of the PFD. The O.A.T. indicator uses an air temperature sensor
located on top of the cabin.
STALL WARNING SYSTEM
The airplane is equipped with a pneumatic-type stall warning system
consisting of an inlet in the leading edge of the left wing, an airoperated horn near the upper left corner of the windshield, and
associated plumbing. As the airplane approaches a stall, the low
pressure on the upper surface of the wings moves forward around the
leading edge of the wings. This low pressure creates a differential
pressure in the stall warning system which draws air through the
warning horn, resulting in a audible warning at 5 to 10 knots above stall
in all flight conditions.
The stall warning system should be checked during the preflight
inspection by applying suction to the system either by placing a clean
handkerchief over the vent opening and applying suction or using some
other type of suction device to activate the warning horn. The system is
operational if the warning horn sounds when suction is applied.
172RPHBUS-00
U.S.
7-67
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
STANDARD AVIONICS
The Garmin G1000 Avionics System is an integrated flight control and
navigation system. The system combines primary flight instruments,
communications, airplane system information and navigational
information all displayed on two color displays. The G1000 system
consists of the following pieces of equipment:
GARMIN DISPLAY UNITS (GDU)
Two identical units are mounted on the instrument panel. One, located
in front of the pilot, is configured as a PFD. A second panel, located to
the right, is configured as a MFD.
The PFD displays roll and pitch information, heading and course
navigation information, plus altitude, airspeed and vertical speed
information to the pilot. The PFD also controls and displays all
communication and navigation frequencies as well as displaying
warning/status annunciations of airplane systems.
The MFD displays a large scalable, moving map that corresponds to
the airplane's current location. Data from other components of the
system can be overlaid on this map. Location and direction of
movement of nearby aircraft, lightning and weather information can all
be displayed on the MFD. The MFD is also the principle display for all
of the engine, fuel, and electrical system parameters.
The reversionary mode places the flight information and basic engine
information on both the PFD and the MFD. This feature allows the pilot
full access to all necessary information should either of the display
screens malfunction.
(Continued Next Page)
7-68
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172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
STANDARD AVIONICS (Continued)
AUDIO PANEL (GMA)
The audio panel for the G1000 system integrates all of the
communication and navigation digital audio signals, intercom system
and marker beacon controls in one unit. It is installed on the instrument
panel between the PFD and the MFD. The audio panel also controls
the reversionary mode for the PFD and MFD.
NOTE
Use of the COM 1/2 function is not approved.
INTEGRATED AVIONICS UNIT (GIA)
Two integrated avionics units are installed in the G1000 system. They
are mounted in racks in the tailcone, behind the baggage curtain.
These units act as the main communications hub linking all of the other
peripheral parts to the GDU displays. Each unit contains a GPS
receiver, a VHF navigation receiver, VHF communication transceiver
and the main system microprocessors. The first GIA unit to acquire a
GPS satellite 3-D navigation signal is the active GPS source.
ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS)
AND MAGNETOMETER (GRS)
The AHRS provides airplane attitude and flight characteristics
information to the G1000 displays and to the integrated avionics units,
which is located in the tailcone of the airplane. The AHRS unit contains
accelerometers, tilt sensors and rate sensors that replace spinning
mass gyros used in other airplanes. The magnetometer is located
inside the left wing panel and interfaces with the AHRS to provide
heading information.
(Continued Next Page)
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7-69
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
STANDARD AVIONICS (Continued)
AIR DATA COMPUTER (GDC)
The Air Data Computer (ADC) compiles information from the airplane's
pitot-static system. The ADC unit is mounted behind the instrument
panel, just forward of the MFD. An outside air temperature probe,
mounted on top of the cabin, is connected to the ADC. The ADC
calculates pressure altitude, airspeed, true airspeed, vertical speed and
outside air temperature.
ENGINE MONITOR (GEA)
The Engine Monitor is responsible for receiving and processing the
signals from all of the engine and airframe sensors. It is connected to
all of the CHT measuring sensors, EGT sensors, RPM, fuel flow and to
the fuel gauging system. This unit transmits this information to the
engine display computers.
TRANSPONDER (GTX)
The full-featured Mode S transponder provides Mode A, C and S
functions. Control and operation of the transponder is accomplished
using the PFD. The transponder unit is mounted in the tailcone avionics
racks.
XM WEATHER AND RADIO DATA LINK (GDL)
The XM weather and radio data link provides weather information and
digital audio entertainment in the cockpit. The unit is mounted in the
tailcone, behind the baggage curtain. This unit communicates with the
MFD on the high-speed data bus. XM weather and XM radio operate in
the S-band frequency range to provide continuous uplink capabilities at
any altitude throughout North America. A subscription to the XM
satellite radio service is required for the XM weather and radio data link
to be used.
(Continued Next Page)
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U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
STANDARD AVIONICS (Continued)
GFC 700 AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS)
(if installed)
Refer to the Garmin G1000 CRG for more information on system
operation.
CONTROL WHEEL STEERING (CWS)
The Control Wheel Steering (CWS) button, located on the pilot’s control
wheel, immediately disconnects the pitch and roll servos when
activated. Large pitch changes while using CWS will cause the airplane
to be out of trim. Retrim the airplane as necessary during CWS
operation to reduce control forces or large pitch oscillations that may
occur after releasing the CWS button.
WARNING
WHEN THE AUTOPILOT IS ENGAGED IN NAV, APR OR
BC OPERATING MODES, IF THE HSI NAVIGATION
SOURCE IS CHANGED MANUALLY, USING THE CDI
SOFTKEY, THE CHANGE WILL INTERRUPT THE
NAVIGATION SIGNAL TO THE AUTOPILOT AND WILL
CAUSE THE AUTOPILOT TO REVERT TO ROL MODE
OPERATION. NO AURAL ALERT WILL BE PROVIDED.
IN ROL MODE, THE AUTOPILOT WILL ONLY KEEP THE
WINGS LEVEL AND WILL NOT CORRECT THE
AIRPLANE HEADING OR COURSE. SET THE HDG BUG
TO THE CORRECT HEADING AND SELECT THE
CORRECT NAVIGATION SOURCE ON THE HSI, USING
THE CDI SOFTKEY, BEFORE ENGAGING THE
AUTOPILOT IN ANY OTHER OPERATING MODE.
(Continued Next Page)
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U.S.
7-71
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
GFC 700 SYSTEM SCHEMATIC
Figure 7-10
7-72
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
AVIONICS SUPPORT EQUIPMENT
Avionics cooling fans, antennas, microphone and headset provisions,
power converter and static discharge wicks support the operation of the
avionics equipment installations.
AVIONICS COOLING FANS
Four DC electric fans provide forced air and ambient air circulation
cooling for the G1000 avionics equipment. A single fan in the tailcone
provides forced air cooling to the integrated avionics units and to the
transponder. A fan located forward of the instrument panel removes air
from between the firewall bulkhead and instrument panel, directing the
warm air up at the inside of the windshield. Two additional fans blow air
directly onto the heat sinks located on the forward sides of the PFD and
MFD.
Power is provided to these fans when the MASTER (BAT) switch and
the AVIONICS (BUS 1 and BUS 2) switch are all ON.
NOTE
None of the cooling fans will operate when the essential
bus avionics equipment is being powered by the standby
battery.
(Continued Next Page)
172RPHBUS-00
U.S.
7-73
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AVIONICS SUPPORT EQUIPMENT (Continued)
ANTENNAS
Two dual-mode VHF COM/GPS antennas are mounted on the top of
the cabin. The COM 1/GPS 1 antenna is mounted on the right side and
the COM 2/GPS 2 antenna is mounted on the left side. They are
connected to the two VHF communication transceivers and the two
GPS receivers in the integrated avionics units.
The GDL antenna is also mounted on the top of the cabin. It provides a
signal to the GDL-69A XM Data Link receiver.
A blade-type navigation antenna is mounted on either side of the
vertical stabilizer. This antenna provides VOR and glideslope signals to
the VHF navigation receivers contained in the integrated avionics units.
The marker beacon antenna is mounted on the bottom of the tailcone.
It provides the signal to the marker beacon receiver located in the audio
panel.
The transponder antenna is mounted on the bottom of the cabin and is
connected to the Mode S transponder by a coaxial transmission cable.
The Bendix/King Distance Measuring Equipment (DME) antenna (if
installed) is mounted on the bottom of the tailcone and is connected to
the Bendix/King DME receiver by a coaxial cable.
(Continued Next Page)
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U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
AVIONICS SUPPORT EQUIPMENT (Continued)
MICROPHONE AND HEADSET INSTALLATIONS
Standard equipment for the airplane includes a hand-held microphone,
an overhead speaker, two remote-keyed microphone switches on the
control wheels, and provisions for communications headsets at each
pilot and passenger station.
The hand-held microphone includes an integral push-to-talk switch.
This microphone is plugged in at the center pedestal and is accessible
to both the pilot and front passenger. Pressing the push-to-talk switch
allows voice transmission on the COM radios.
The overhead speaker is located in the center overhead console.
Volume and output for this speaker are controlled through the audio
panel.
Each control wheel contains a push-to-talk switch. This switch allows
the pilot or front passenger to transmit on the COM radios using remote
microphones.
Each seat position of the airplane has provisions for aviation-style
headsets. Microphone and headphone jacks are located on each
respective sidewall panel for communications between passengers and
pilot. The system is designed so that microphones are voice activated.
Only the pilot or front passenger can transmit through the COM radios.
NOTE
To ensure audibility and clarity when transmitting with the
hand-held microphone, always hold it as closely as possible
to the lips, then press the transmit switch and speak directly
into it. Avoid covering the opening on the back side of
microphone for optimum noise canceling.
(Continued Next Page)
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7-75
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AVIONICS SUPPORT EQUIPMENT (Continued)
AUXILIARY AUDIO INPUT JACK
An auxiliary audio input jack (AUX AUDIO IN) is located on the center
pedestal, Refer to Figure 7-2. It allows entertainment audio devices
such as cassette, compact disc, and MP3 players to play music over
the airplane's headsets.
The signal from AUX AUDIO IN is automatically muted during radio
communications or pilot selection of crew intercom isolation modes
located on the audio panel. The AUX key on the audio panel does not
control the AUX AUDIO IN signal. For a more complete description and
operating instructions of the audio panel, refer to the Garmin G1000
CRG.
Since the entertainment audio input is not controlled by a switch, there
is no way to deselect the entertainment source except to disconnect the
source at the audio input connector. In the event of a high pilot
workload and/or heavy traffic, it is wise to disable the entertainment
audio to eliminate a source of distraction for the flight crew.
NOTE
•
Passenger briefing should specify that AUX AUDIO IN
(entertainment audio input) and Portable Electronic
Device (PED) use is permitted only during the enroute
phase of flight.
•
Disconnect the cable from the AUX AUDIO IN jack when
not in use.
•
Use caution with audio cables in the cabin to avoid
entangling occupants or cabin furnishings and to prevent
damage to cables.
(Continued Next Page)
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172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
AVIONICS SUPPORT EQUIPMENT (Continued)
12V POWER OUTLET
A power converter, located on the cabin side of the firewall just forward
of the right instrument panel, reduces the airplane's 28 VDC power to
12 VDC. This converter provides up to 10 amps of power to operate
portable devices such as notebook computers and audio players. The
power output connector (POWER OUTLET 12V -10A) is located on the
center pedestal, Refer to Figure 7-2.
A switch located on the switch panel labeled CABIN PWR 12V controls
the operation of the power outlet.
NOTE
•
Charging of lithium batteries may cause the lithium
batteries to explode.
•
Take care to observe the manufacturer's power
requirements prior to plugging any device into the 12 volt
cabin power system connector. This system is limited to
a maximum of 10 amps.
•
Use caution with power/adapter cables in the cabin to
avoid entangling occupants or cabin furnishings and to
prevent damage to cables supplying live electric current.
•
Disconnect power/adapter cables when not in use.
(Continued Next Page)
172RPHBUS-00
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7-77
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AVIONICS SUPPORT EQUIPMENT (Continued)
STATIC DISCHARGERS
Static dischargers are installed at various points throughout the
airframe to reduce interference from precipitation static. Under some
severe static conditions, loss of radio signals is possible even with
static dischargers installed. Whenever possible, avoid known severe
precipitation areas to prevent loss of dependable radio signals. If
avoidance is impractical, minimize airspeed and anticipate temporary
loss of radio signals while in these areas.
Static dischargers lose their effectiveness with age, and therefore,
should be checked periodically, at least at every annual inspection, by a
qualified technician.
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MODEL 172R NAV III
GFC 700 AFCS
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CABIN FEATURES
EMERGENCY LOCATOR TRANSMITTER (ELT)
Refer to Section 9, Supplements 1 or 2 for appropriate ELT operating
information.
CABIN FIRE EXTINGUISHER
A portable Halon 1211 (Bromochlorodifluoromethane) fire extinguisher
is installed in a holder on the floorboard between the front seats to be
accessible in case of fire. The extinguisher is classified 5B:C by
Underwriters Laboratories.
The extinguisher should be checked prior to each flight to ensure that
the pressure of the contents, as indicated by the gage at the top of the
extinguisher, is within the green arc (approximately 125 psi) and the
operating lever lock pin is securely in place.
To operate the fire extinguisher:
1. Loosen retaining clamp(s) and remove extinguisher from bracket.
2. Hold extinguisher upright, pull operating ring pin, and press lever
while directing the liquid at the base of the fire at the near edge.
Progress toward the back of the fire by moving the nozzle rapidly
with a side-to-side sweeping motion.
WARNING
VENTILATE
THE
CABIN
PROMPTLY
AFTER
SUCCESSFULLY EXTINGUISHING THE FIRE TO
REDUCE THE GASES PRODUCED BY THERMAL
DECOMPOSITION.
3. The contents of the cabin fire extinguisher will empty in
approximately eight seconds of continuous use.
Fire extinguishers should be recharged by a qualified fire extinguisher
agency after each use. After recharging, secure the extinguisher to its
mounting bracket.
(Continued Next Page)
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U.S.
7-79
SECTION 7
AIRPLANE AND SYSTEM DESCRIPTION
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CABIN FEATURES (Continued)
CARBON MONOXIDE DETECTION SYSTEM
The carbon monoxide (CO) detection system consist of a single
detector located behind the instrument panel, powered by the
airplane’s DC electrical system and integrated in the Garmin G1000
system with a warning annunciation and alert messages displayed on
the PFD.
When the CO detection system senses a CO level of 50 parts-permillion (PPM) by volume or greater the alarm turns on a flashing
warning annunciation, CO LVL HIGH, in the annunciation window on
the PFD with a continuous tone until the PFD softkey below WARNING
is pushed. It then remains on steady until the CO level drops below 50
PPM and automatically resets the alarm.
If the CO system detects a problem within the system that requires
service, a CO DET SRVC message is displayed in the alerts window of
the PFD. If there is an interface problem between the G1000 system
and the CO system a CO DET FAIL message is displayed in the alerts
window of the PFD.
7-80
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172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
TABLE OF CONTENTS
Page
Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-3
Identification Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-4
Cessna Owner Advisories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-4
United States Airplane Owners . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-4
International Airplane Owners . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-4
Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-5
Airplane File. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-6
Airplane Inspection Periods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-7
FAA Required Inspections. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-7
Cessna Inspection Programs . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-7
Cessna Customer Care Program . . . . . . . . . . . . . . . . . . . . . . . . . 8-8
Pilot Conducted Preventive Maintenance . . . . . . . . . . . . . . . . . . . . . 8-8
Alterations Or Repairs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-9
Ground Handling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-9
Towing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-9
Parking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-9
Tiedown. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-10
Jacking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .8-10
Leveling. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-11
Flyable Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-11
Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-12
Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-13
Oil Specification. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-13
Recommended Viscosity For Temperature Range . . . . . . . . . . . 8-13
Capacity Of Engine Sump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-14
Oil And Oil Filter Change . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-14
(Continued Next Page)
172RPHBUS-00
U.S.
8-1
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
TABLE OF CONTENTS
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
(Continued)
Page
Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-15
Approved Fuel Grades (And Colors) . . . . . . . . . . . . . . . . . . . . . 8-15
Fuel Capacity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-15
Fuel Additives . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-16
Fuel Contamination . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-20
Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-21
Cleaning And Care . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-22
Windshield And Windows . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-22
Painted Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-23
Propeller Care . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-24
Engine Care. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-24
Interior Care. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-25/8-26
Avionics Care. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-25/8-26
8-2
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
INTRODUCTION
This section contains factory recommended procedures for proper
ground handling and routine care and servicing of your airplane. It also
identifies certain inspection and maintenance requirements which must
be followed if your airplane is to retain that new airplane performance
and dependability. It is important to follow a planned schedule of
lubrication and preventive maintenance based on climatic and flying
conditions encountered in your local area.
Keep in touch with a Cessna Service Station and take advantage of
their knowledge and experience. Your Cessna Service Station knows
your airplane and how to maintain it, and will remind you when
lubrications and oil changes are necessary, as well as other seasonal
and periodic services.
The airplane should be regularly inspected and maintained in
accordance with information found in the airplane maintenance manual
and in company issued service bulletins and service newsletters. All
service bulletins pertaining to the airplane by serial number should be
accomplished and the airplane should receive repetitive and required
inspections. Cessna does not condone modifications, whether by
Supplemental Type Certificate (STC) or otherwise, unless these
certificates are held and/or approved by Cessna. Other modifications
may void warranties on the airplane since Cessna has no way of
knowing the full effect on the overall airplane. Operation of an airplane
that has been modified may be a risk to the occupants, and operating
procedures and performance data set forth in the POH may no longer
be considered accurate for the modified airplane.
172RPHBUS-00
U.S.
8-3
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
IDENTIFICATION PLATE
All correspondence regarding your airplane should include the Serial
Number. The Serial Number, Model Number, Production Certificate
Number (PC) and Type Certificate Number (TC) can be found on the
Identification Plate, located on the aft left tailcone. The Finish and Trim
Plate, which is installed on the lower part of the left forward doorpost,
contains a code describing the exterior paint combination of the
airplane. The code may be used in conjunction with an applicable
Illustrated Parts Catalog if finish and trim information is needed.
CESSNA OWNER ADVISORIES
Cessna Owner Advisories are sent to Cessna Aircraft FAA Registered
owners of record at no charge to inform them about mandatory and/or
beneficial airplane service requirements and product changes. Copies
of the actual bulletins are available from Cessna Service Stations and
Cessna Propeller Aircraft Customer Services.
UNITED STATES AIRPLANE OWNERS
If your airplane is registered in the U.S., appropriate Cessna Owner
Advisories will be mailed to you automatically according to the latest
airplane registration name and address which you have provided to the
FAA. Therefore, it is important that you provide correct and up to date
mailing information to the FAA.
If you require a duplicate Owner Advisory to be sent to an address
different from the FAA aircraft registration address, please complete
and return an Owner Advisory Application (otherwise no action is
required on your part).
INTERNATIONAL AIRPLANE OWNERS
To receive Cessna Owner Advisories, please complete and return an
Owner Advisory Application.
Receipt of a valid Owner Advisory Application will establish your
Cessna Owner Advisory service for one year, after which you will be
sent a renewal notice. It is important that you respond promptly to
update your address for this critical service.
8-4
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
PUBLICATIONS
Various publications and flight operation aids are furnished in the
airplane when delivered from the factory. These items are listed below.
•
•
Customer Care Program Handbook
•
•
•
Pilot’s Checklist
Pilot’s Operating Handbook and FAA Approved Airplane
Flight Manual
Passenger Briefing Card
Cessna Service Station Directory
To obtain additional publications or owner advisory information, you
may contact Cessna Propeller Aircraft Customer Services at (316) 5175800, Fax (316) 517-7271 or write to Cessna Aircraft Company, P.O.
Box 7706, Wichita, KS 67277, Dept 751C.
The following additional publications, plus many other supplies that are
applicable to your airplane, are available from a Cessna Service
Station.
•
Information Manual (contains
Handbook Information)
•
Maintenance Manual, Wiring Diagram Manual and
Illustrated Parts Catalog
Pilot’s
Operating
Cessna Service Stations have a Customer Care Supplies and
Publications Catalog covering all available items, many of which the
Service Station keeps on hand. The Service Station can place an order
for any item which is not in stock.
NOTE
A Pilot's Operating Handbook and FAA Approved Airplane
Flight Manual which is lost or destroyed may be replaced by
contacting a Cessna Service Station. An affidavit containing
the owner's name, airplane serial number and reason for
replacement must be included in replacement requests
since the Pilot's Operating Handbook and FAA Approved
Airplane Flight Manual is identified for specific serial
numbered airplanes only.
172RPHBUS-00
U.S.
8-5
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AIRPLANE FILE
There are miscellaneous data, information and licenses that are a part
of the airplane file. The following is a checklist for that file. In addition, a
periodic check should be made of the latest Federal Aviation
Regulations to ensure that all data requirements are met.
To be displayed in the airplane at all times:
1. Aircraft Airworthiness Certificate (FAA Form 8100-2)
2. Aircraft Registration Certificate (FAA Form 8050-3)
3. Aircraft Radio Station License, (if applicable)
To be carried in the airplane at all times:
1. Current Pilot's Operating Handbook and FAA Approved Airplane
Flight Manual
2. Garmin G1000 Cockpit Reference Guide (190-00384-00 Rev. B
or subsequent)
3. Weight and Balance, and associated papers (latest copy of the
Repair and Alteration Form, FAA Form 337, if applicable)
4. Equipment List
To be made available upon request:
1. Airplane Logbook
2. Engine Logbook
Most of the items listed are required by the United States Federal
Aviation Regulations. Since the regulations of other nations may
require other documents and data, owners of airplanes not registered in
the United States should check with their own aviation officials to
determine their individual requirements.
Cessna recommends that these items, plus the Pilot's Checklists,
Customer Care Program Handbook and Customer Care Card, be
carried in the airplane at all times.
8-6
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
AIRPLANE INSPECTION PERIODS
FAA REQUIRED INSPECTIONS
As required by U.S. Federal Aviation Regulations, all civil aircraft of
U.S. registry must undergo a complete inspection (annual) each twelve
calendar months. In addition to the required annual inspection, aircraft
operated commercially (for hire) must have a complete inspection
every 100 hours of operation.
The FAA may require other inspections by the issuance of
airworthiness directives applicable to the airplane, engine, propeller
and components. It is the responsibility of the owner/operator to ensure
compliance with all applicable airworthiness directives, and when the
inspections are repetitive, to take appropriate steps to prevent
inadvertent noncompliance.
CESSNA INSPECTION PROGRAMS
In lieu of the 100 hour and annual inspection requirements, an airplane
may be inspected in accordance with a Progressive Care Inspection
Program or a PhaseCard Inspection Program. Both programs offer
systems which allow the work load to be divided into smaller operations
that can be accomplished in shorter time periods.
The Cessna Progressive Care Inspection Program allows an airplane
to be inspected and maintained in four operations. The four operations
are recycled each 200 hours and are recorded in a specially provided
Aircraft Inspection Log as each operation is conducted.
The PhaseCard Inspection Program offers a parallel system for highutilization flight operations (approximately 600 flight hours per year).
This system utilizes 50 hour intervals (Phase 1 and Phase 2) to inspect
high-usage systems and components. At 12 months or 600 flight hours,
whichever occurs first, the airplane undergoes a complete (Phase 3)
inspection.
Regardless of the inspection method selected, the owner should keep
in mind that 14 CFR 43 and 14 CFR 91 establishes the requirement
that properly certified agencies or personnel accomplish all required
FAA inspections and most of the manufacturer recommended
inspections.
(Continued Next Page)
172RPHBUS-00
U.S.
8-7
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AIRPLANE INSPECTION PERIODS (Continued)
CESSNA CUSTOMER CARE PROGRAM
Specific benefits and provisions of the Cessna Warranty plus other
important benefits for you are contained in your Customer Care
Program Handbook supplied with your airplane. The Customer Care
Program Handbook should be thoroughly reviewed and kept in the
airplane at all times.
You will also want to return to your Cessna Service Station either at 50
hours for your first Progressive Care Operation, or at 100 hours for your
first 100 hour inspection depending on which program you choose to
establish for your airplane. While these important inspections will be
performed for you by any Cessna Service Station, in most cases you
will prefer to have the Cessna Service Station from whom you
purchased the airplane accomplish this work.
PILOT CONDUCTED PREVENTIVE MAINTENANCE
A certified pilot who owns or operates an airplane not used as an air
carrier is authorized by 14 CFR 43 to perform limited maintenance on
his airplane. Refer to 14 CFR 43 for a list of the specific maintenance
operations which are allowed.
NOTE
Pilots operating airplanes of other than U.S. registry should
refer to the regulations of the country of certification for
information on preventive maintenance that may be
performed by pilots.
A Maintenance Manual must be obtained prior to performing any
preventive maintenance to ensure that proper procedures are followed.
A Cessna Service Station should be contacted for further information or
for required maintenance which must be accomplished by appropriately
licensed personnel.
8-8
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
ALTERATIONS OR REPAIRS
It is essential that the FAA be contacted prior to any alterations on the
airplane to ensure that airworthiness of the airplane is not violated.
Alterations or repairs to the airplane must be accomplished by licensed
personnel, utilizing only FAA Approved components and FAA Approved
data, such as Cessna Service Bulletins.
GROUND HANDLING
TOWING
The airplane is most easily and safely maneuvered by hand with the
tow bar attached to the nosewheel (the tow bar is stowed on the side of
the baggage area). When towing with a vehicle, do not exceed the
nose gear turning angle of 30° either side of center, or damage to the
nose landing gear will result.
CAUTION
REMOVE ANY INSTALLED RUDDER LOCK BEFORE
TOWING.
If the airplane is towed or pushed over a rough surface during
hangaring, watch that the normal cushioning action of the nose strut
does not cause excessive vertical movement of the tail and the
resulting contact with low hangar doors or structure. A flat nose tire or
deflated strut will also increase tail height.
PARKING
When parking the airplane, head into the wind and set the parking
brake. Do not set the parking brake during cold weather when
accumulated moisture may freeze the brakes, or when the brakes are
overheated. Install the control wheel lock and chock the wheels. In
severe weather and high wind conditions, tie the airplane down as
outlined in the following paragraph.
(Continued Next Page)
172RPHBUS-00
U.S.
8-9
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
GROUND HANDLING (Continued)
TIEDOWN
Proper tiedown procedure is the best precaution against damage to the
parked airplane by gusty or strong winds. To tiedown the airplane
securely, proceed as follows:
1. Set the parking brake and install the control wheel lock.
2. Install a surface control lock over the fin and rudder.
3. Tie sufficiently strong ropes or chains (700 pounds tensile
strength) to the wing, tail and nose tiedown fittings and secure
each rope or chain to a ramp tiedown.
4. Install a pitot tube cover.
JACKING
When a requirement exists to jack the entire airplane off the ground, or
when wing jack points are used in the jacking operation, refer to the
Maintenance Manual for specific procedures and equipment required.
Individual main gear may be jacked by using the jack pad which is
incorporated in the main landing gear strut step bracket. When using
the individual gear strut jack pad, flexibility of the gear strut will cause
the main wheel to slide inboard as the wheel is raised, tilting the jack.
The jack must then be lowered for a second jacking operation. Do not
jack both main wheels simultaneously using the individual main gear
jack pads.
CAUTION
DO NOT APPLY PRESSURE ON THE ELEVATOR OR
H O R I Z O N TA L S TA B I L I Z E R S U R FA C E S . W H E N
P U S H I N G O N T H E TA I L C O N E , A LWAY S A P P LY
PRESSURE AT A BULKHEAD TO AVOID BUCKLING THE
SKIN.
If nose gear maintenance is required, the nosewheel may be raised off
the ground by pressing down on a tailcone bulkhead, just forward of the
horizontal stabilizer, and allowing the tail to rest on the tail tiedown ring.
(Continued Next Page)
8-10
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
GROUND HANDLING
(Continued)
JACKING (Continued)
To assist in raising and holding the nosewheel off the ground, ground
anchors should be utilized at the tail tiedown point.
NOTE
Ensure that the nose will be held off the ground under all
conditions by means of suitable stands or supports under
weight supporting bulkheads near the nose of the airplane.
LEVELING
Longitudinal leveling of the airplane is accomplished by placing a level
on leveling screws located on the left side of the tailcone. Deflate the
nose tire and/or lower or raise the nose strut to properly center the
bubble in the level. Corresponding points on both upper door sills may
be used to level the airplane laterally.
FLYABLE STORAGE
Engines in airplanes that are flown every 30 days or less may not
achieve normal service life because of internal corrosion. Corrosion
occurs when moisture from the air and the products of combustion
combine to attack cylinder walls and bearing surfaces during periods
when the airplane is not flown.
The minimum recommended operating frequency for the engine is one
continuous flight hour (not counting taxi, takeoff and landing time) with
oil temperatures of 165°F to 200°F every 30 days or less (depending on
location and storage conditions). Airplanes operated close to oceans,
lakes, rivers and in humid regions are in greater need of engine
preservation than airplanes operated in arid regions. Appropriate
engine preservation procedures must be practiced by the owner or
operator of the airplane based on present environmental conditions and
the frequency of airplane activity.
NOTE
The engine manufacturer does not recommend pulling the
engine through by hand during storage periods.
(Continued Next Page)
172RPHBUS-00
U.S.
8-11
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
GROUND HANDLING (Continued)
FLYABLE STORAGE (Continued)
If the airplane is to remain inactive for more than 30 days, consult the
latest revision of Textron Lycoming Service Letter L180
(www.lycoming.textron.com).
It is recommended when storing the airplane for any period of time to
keep fuel tanks full to minimize condensation in tanks. Keep the battery
fully charged to prevent the electrolyte from freezing in cold weather.
Refer to the Maintenance Manual for proper airplane storage
procedures.
SERVICING
In addition to the Preflight Inspection covered in Section 4 of this POH,
complete servicing, inspection and test requirements for your airplane
are detailed in the Maintenance Manual. The Maintenance Manual
outlines all items which require attention at specific intervals plus those
items which require servicing, inspection, and/or testing at special
intervals.
Since Cessna Service Stations conduct all service, inspection, and test
procedures in accordance with applicable Maintenance Manuals, it is
recommended that you contact a Cessna Service Station concerning
these requirements and begin scheduling your airplane for service at
the recommended intervals.
Cessna Progressive Care ensures that these requirements are
accomplished at the required intervals to comply with the 100 hour or
annual inspection as previously covered.
Depending on various flight operations, your local government aviation
agency may require additional service, inspections, or tests. For these
regulatory requirements, owners should check with local aviation
officials where the airplane is being operated.
For quick and ready reference, quantities, materials and specifications
for frequently used service items are as follows.
8-12
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
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 Textron Lycoming Service Instruction No 1014, and all
revisions and supplements thereto, must be used after first 50 hours
or oil consumption has stabilized.
RECOMMENDED
RANGE
VISCOSITY
FOR
TEMPERATURE
Multiviscosity or straight grade oil may be used throughout the year for
engine lubrication. Refer to the following table for temperature versus
viscosity ranges.
Temperature
Above 27°C (80°F)
Above 16°C (60°F)
-1°C (30°F) to 32°C (90°F)
-18°C (0°F) to 21°C (70°F)
Below -12°C (10°F)
-18°C (0°F) to 32°C (90°F)
All Temperatures
MIL-L-6082
MIL-L-22851
or SAE J1966
or SAE J1899
Straight Mineral Oil Ashless Dispersant Oil
SAE Grade
SAE Grade
60
50
40
30
20
20W-50
---
60
40 or 50
40
30, 40 or 20W-40
30 or 20W-30
20W-50 or 15W-50
15W-50 or 20W-50
NOTE
When operating temperatures overlap, use the lighter
grade of oil.
(Continued Next Page)
172RPHBUS-00
U.S.
8-13
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
OIL (Continued)
CAPACITY OF ENGINE SUMP
The engine has a total capacity of 9 quarts, with the oil filter accounting
for approximately 1 quart of that total. The engine oil sump has a
capacity of 8 quarts. The engine must not be operated on less than 5
quarts (as measured by the dipstick). For extended flights, the engine
should be filled to capacity.
OIL AND OIL FILTER CHANGE
After the first 25 hours of operation, drain the engine oil sump and
replace the filter. Refill sump with straight mineral oil and use until a
total of 50 hours has accumulated or oil consumption has stabilized;
then change to ashless dispersant oil. Ashless dispersant oil (and oil
filter) should be changed at time intervals set forth by the engine
manufacturer.
NOTE
During the first 25 hour oil and filter change, a general
inspection of the overall engine compartment is required.
Items which are not normally checked during a preflight
inspection should be given special attention. Hoses, metal
lines and fittings should be inspected for signs of oil and
fuel leaks, and checked for abrasions, chafing, security,
proper routing and support, and evidence of deterioration.
Inspect the intake and exhaust systems for cracks,
evidence of leakage, and security of attachment. Engine
controls and linkages should be checked for freedom of
movement through their full range, security of attachment
and evidence of wear. Inspect wiring for security, chafing,
burning, defective insulation, loose or broken terminals,
heat deterioration, and corroded terminals. Check the
alternator belt in accordance with Maintenance Manual
instructions, and retighten if necessary. A periodic check of
these items during subsequent servicing operations is
recommended.
8-14
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
FUEL
APPROVED FUEL GRADES (AND COLORS)
100LL Grade Aviation Fuel (Blue)
100
Grade Aviation Fuel (Green)
NOTE
Isopropyl alcohol or Diethylene Glycol Monomethyl Ether
(DiEGME) may be added to the fuel supply in quantities not
to exceed 1% (alcohol) or 0.15% (DiEGME) of total volume.
Refer to Fuel Additives in later paragraphs for additional
information.
FUEL CAPACITY
56.0 U.S. Gallons Total: . . . . . . . . . . . . 28.0 U.S. Gallons per tank.
NOTE
•
To ensure maximum fuel capacity when refueling and
minimize crossfeeding, the fuel selector valve should be
placed in either the LEFT or RIGHT position and the
airplane parked in a wings level, normal ground attitude.
Refer to Figure 1-1 for a definition of normal ground
attitude.
•
Service the fuel system after each flight, and keep fuel
tanks full to minimize condensation in the tanks.
(Continued Next Page)
172RPHBUS-00
U.S.
8-15
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
FUEL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
(Continued)
FUEL ADDITIVES
Strict adherence to recommended preflight draining instructions as
called for in Section 4 will eliminate any free water accumulations from
the tank sumps. While small amounts of water may still remain in
solution in the gasoline, it will normally be consumed and go unnoticed
in the operation of the engine.
One exception to this can be encountered when operating under the
combined effect of: (1) use of certain fuels, with (2) high humidity
conditions on the ground (3) followed by flight at high altitude and low
temperature. Under these unusual conditions, small amounts of water
in solution can precipitate from the fuel stream and freeze in sufficient
quantities to induce partial icing of the engine fuel system.
While these conditions are quite rare and will not normally pose a
problem to owners and operators, they do exist in certain areas of the
world and consequently must be dealt with, when encountered.
Therefore, to help alleviate the possibility of fuel icing occurring under
these unusual conditions, it is permissible to add isopropyl alcohol or
Diethylene Glycol Monomethyl Ether (DiEGME) compound to the fuel
supply.
The introduction of alcohol or DiEGME compound into the fuel provides
two distinct effects: (1) it absorbs the dissolved water from the gasoline
and (2) alcohol has a freezing temperature depressant effect.
NOTE
When using fuel additives, it must be remembered that the
final goal is to obtain a correct fuel to additive ratio in the
tank, and not just with fuel coming out of the refueling
nozzle. For example, adding 15 gallons of correctly
proportioned fuel to a tank which contains 20 gallons of
untreated fuel will result in a lower than acceptable
concentration level to the 35 gallons of fuel which now
reside in the tank.
(Continued Next Page)
8-16
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FUEL
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
(Continued)
FUEL ADDITIVES (Continued)
Alcohol, if used, is to be blended with the fuel in a concentration of 1%
by volume. Concentrations greater than 1% are not recommended
since they can be detrimental to fuel tank materials.
The manner in which the alcohol is added to the fuel is significant
because alcohol is most effective when it is completely dissolved in the
fuel. To ensure proper mixing, the following is recommended:
1. For best results, the alcohol should be added during the fueling
operation by pouring the alcohol directly on the fuel stream
issuing from the fueling nozzle.
2. An alternate method that may be used is to premix the complete
alcohol dosage with some fuel in a separate clean container
(approximately 2-3 gallon capacity) and then transferring this
mixture to the tank prior to the fuel operation.
(Continued Next Page)
172RPHBUS-00
U.S.
8-17
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FUEL MIXING RATIO
Figure 8-1
8-18
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
FUEL
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
(Continued)
FUEL ADDITIVES (Continued)
Diethylene Glycol Monomethyl Ether (DiEGME) compound must be
carefully mixed with the fuel in concentrations between 0.10%
(minimum) and 0.15% (maximum) of total fuel volume. Refer to Figure
8-1 for a DiEGME-to-fuel mixing chart.
WARNING
ANTI-ICING ADDITIVE IS DANGEROUS TO HEALTH
WHEN BREATHED AND/OR ABSORBED INTO THE
SKIN.
CAUTION
MI XI NG O F DI EG ME WI TH FUEL I S EXTR EMELY
IMPORTANT. A CONCENTRATION IN EXCESS OF THAT
RECOMMENDED (0.15% BY VOLUME MAXIMUM) MAY
RESULT IN DETRIMENTAL EFFECTS TO THE FUEL
TANK AND SEALANT, AND DAMAGE TO O-RINGS AND
SEALS USED IN THE FUEL SYSTEM AND ENGINE
COMPONENTS. A CONCENTRATION OF LESS THAN
THAT RECOMMENDED (0.10% BY TOTAL VOLUME
MINIMUM) WILL RESULT IN INEFFECTIVE TREATMENT.
U S E O N LY B L E N D I N G E Q U I P M E N T T H AT I S
RECOMMENDED BY THE MANUFACTURER TO OBTAIN
PROPER PROPORTIONING.
Prolonged storage of the airplane will result in a water buildup in the
fuel which leeches out the additive. An indication of this is when an
excessive amount of water accumulates in the fuel tank sumps. The
concentration can be checked using a differential refractometer. It is
imperative that the technical manual for the differential refractometer be
followed explicitly when checking the additive concentration.
(Continued Next Page)
172RPHBUS-00
U.S.
8-19
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
FUEL
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
(Continued)
FUEL CONTAMINATION
Fuel contamination is usually the result of foreign material present in
the fuel system, and may consist of water, rust, sand, dirt, microbes or
bacterial growth. In addition, additives that are not compatible with fuel
or fuel system components can cause the fuel to become
contaminated.
Before each flight and after each refueling, use a clear sampler cup and
drain at least a cupful of fuel from each fuel tank drain location and from
the fuel strainer quick drain valve to determine if contaminants are
present, and to ensure the airplane has been fueled with the proper
grade of fuel.
If contamination is detected, drain all fuel drain points again, including
the fuel reservoir tank and fuel selector drain valves, and then gently
rock the wings and lower the tail to the ground to move any additional
contaminants to the sampling points. Take repeated samples from all
fuel drain points until all contamination has been removed. If, after
repeated sampling, evidence of contamination still exists, the airplane
should not be flown. Tanks should be drained and system purged by
qualified maintenance personnel. All evidence of contamination must
be removed before further flight. If the airplane has been serviced with
the improper fuel grade, defuel completely and refuel with the correct
grade. Do not fly the airplane with contaminated or unapproved fuel.
In addition, Owners/Operators who are not acquainted with a particular
fixed base operator should be assured that the fuel supply has been
checked for contamination and is properly filtered before allowing the
airplane to be serviced. Fuel tanks should be kept full between flights,
provided weight and balance considerations will permit, to reduce the
possibility of water condensing on the walls of partially filled tanks.
To further reduce the possibility of contaminated fuel, routine
maintenance of the fuel system should be performed in accordance
with the airplane Maintenance Manual. Only the proper fuel, as
recommended in this POH, should be used, and fuel additives should
not be used unless approved by Cessna and the Federal Aviation
Administration.
8-20
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
LANDING GEAR
Consult the following table for servicing information on the landing gear.
COMPONENT
SERVICING CRITERIA
Nose Wheel (5.00-5, 6-Ply Rated Tire)
34.0 PSI
Main Wheel (6.00-6, 4-Ply Rated Tire)
29.0 PSI
Brakes
MIL-H-5606
Nose Gear Shock Strut
MIL-H-5606; 45.0 PSI *
* Keep strut filled with MIL-H-5606 hydraulic fluid per
filling instructions placard, and with no load on the strut,
inflate with air to 45.0 PSI. Do not over inflate.
172RPHBUS-00
U.S.
8-21
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CLEANING AND CARE
WINDSHIELD AND WINDOWS
The plastic windshield and windows should be cleaned with an airplane
windshield cleaner. Apply the cleaner sparingly with soft cloths, and rub
with moderate pressure until all dirt, oil scum and bug stains are
removed. Allow the cleaner to dry, then wipe it off with soft flannel
cloths.
CAUTION
NEVER USE GASOLINE, BENZENE, ALCOHOL,
ACETONE, FIRE EXTINGUISHER, ANTI-ICE FLUID,
LACQUER THINNER OR GLASS CLEANER TO CLEAN
THE PLASTIC. THESE MATERIALS WILL ATTACK THE
PLASTIC AND MAY CAUSE IT TO CRAZE.
If a windshield cleaner is not available, the plastic can be cleaned with
soft cloths moistened with Stoddard solvent to remove oil and grease.
Follow by carefully washing with a mild detergent and plenty of water.
Rinse thoroughly, then dry with a clean moist chamois.
Do not rub the plastic with a dry cloth since this builds up an
electrostatic charge which attracts dust. Waxing with a good
commercial wax will finish the cleaning job. A thin, even coat of wax,
polished out by hand with clean soft flannel cloths, will fill in minor
scratches and help prevent further scratching.
Do not use a canvas cover on the windshield unless freezing rain or
sleet is anticipated since the cover may scratch the plastic surface.
(Continued Next Page)
8-22
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CLEANING AND CARE (Continued)
PAINTED SURFACES
The painted exterior surfaces of your new Cessna have a durable, long
lasting finish.
Generally, the painted surfaces can be kept bright by washing with
water and mild soap, followed by a rinse with water and drying with
cloths or a chamois. Harsh or abrasive soaps or detergents which
cause corrosion or scratches should never be used. Remove stubborn
oil and grease with a cloth moistened with Stoddard solvent. Take
special care to make sure that the exterior graphics are not touched by
the solvent. For complete care of exterior graphics, refer to the
Maintenance Manual.
To seal any minor surface chips or scratches and protect against
corrosion, the airplane should be waxed regularly with a good
automotive wax applied in accordance with the manufacturer's
instructions. If the airplane is operated in a seacoast or other salt water
environment, it must be washed and waxed more frequently to assure
adequate protection. Special care should be taken to seal around rivet
heads and skin laps, which are the areas most susceptible to corrosion.
A heavier coating of wax on the leading edges of the wings and tail and
on the cowl nose cap and propeller spinner will help reduce the
abrasion encountered in these areas. Reapplication of wax will
generally be necessary after cleaning with soap solution or after
chemical deicing operations.
When the airplane is parked outside in cold climates and it is necessary
to remove ice before flight, care should be taken to protect the painted
surfaces during ice removal with chemical liquids. Isopropyl alcohol will
satisfactorily remove ice accumulations without damaging the paint.
However, keep the isopropyl alcohol away from the windshield and
cabin windows since it will attack the plastic and may cause it to craze.
(Continued Next Page)
172RPHBUS-00
U.S.
8-23
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
CLEANING AND CARE (Continued)
PROPELLER CARE
Preflight inspection of propeller blades for nicks, and wiping them
occasionally with an oily cloth to clean off grass and bug stains will
assure long blade life. Small nicks on the propeller, particularly near the
tips and on the leading edges, should be dressed out as soon as
possible since these nicks produce stress concentrations, and if
ignored, may result in cracks or failure of the propeller blade. Never use
an alkaline cleaner on the blades; remove grease and dirt with
Stoddard solvent.
ENGINE CARE
The engine may be cleaned, using a suitable solvent, in accordance
with instructions in the Maintenance Manual. Most efficient cleaning is
done using a spray type cleaner. Before spray cleaning, ensure that
protection is afforded for components which might be adversely
affected by the solvent. Refer to the airplane Maintenance Manual for
proper lubrication of controls and components after engine cleaning.
The induction air filter should be replaced when its condition warrants,
not to exceed 500 hours.
(Continued Next Page)
8-24
U.S.
172RPHBUS-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 8
AIRPLANE HANDLING, SERVICE
AND MAINTENANCE
CLEANING AND CARE (Continued)
INTERIOR CARE
To remove dust and loose dirt from the upholstery and carpet, clean the
interior regularly with a vacuum cleaner.
Blot up any spilled liquid promptly with cleansing tissue or rags. Do not
pat the spot; press the blotting material firmly and hold it for several
seconds. Continue blotting until no more liquid is taken up. Scrape off
sticky materials with a dull knife, then spot clean the area.
Oily spots may be cleaned with household spot removers, used
sparingly. Before using any solvent, read the instructions on the
container and test it on an obscure place on the fabric to be cleaned.
Never saturate the fabric with a volatile solvent; it may damage the
padding and backing materials.
Soiled upholstery and carpet may be cleaned with foam type detergent,
used according to the manufacturer's instructions. To minimize wetting
the fabric, keep the foam as dry as possible and remove it with a
vacuum cleaner.
For complete information related to interior cleaning, refer to the
Maintenance Manual.
AVIONICS CARE
The Garmin GDU displays have an anti-reflective coating that is very
sensitive to skin oils, waxes, ammonia, and abrasive cleaners. Clean
the displays as described in the G1000 Cockpit Reference Guide.
172RPHBUS-00
U.S.
8-25/8-26
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9
SUPPLEMENTS
SUPPLEMENTS
INTRODUCTION
The supplements in this section contain amended operating limitations,
operating procedures, performance data and other necessary
information for airplanes conducting special operations for both
standard and optional equipment installed in the airplane. Operators
should refer to each supplement to ensure that all limitations and
procedures appropriate for their airplane are observed.
A non FAA Approved Log Of Approved Supplements is provided for
convenience only. This log is a numerical list of all FAA Approved
supplements applicable to this airplane by name, supplement number
and revision level. This log should be used as a checklist to ensure all
applicable supplements have been placed in the Pilot's Operating
Handbook (POH). Supplements for both standard and installed optional
equipment must be maintained to the latest revision. Those
supplements applicable to optional equipment which is not installed in
the airplane, do not have to be retained.
Each individual supplement contains its own Log of Effective Pages.
This log lists the page number and revision level of every page in the
supplement. The log also lists the dates on which revisions to the
supplement occurred. Supplement page numbers will include an S and
the supplement number preceding the page number.
The part number of the supplement provides information on the
revision level. Refer to the following example:
172RPHBUS
-S1 -00
Revision Level of Supplement
Supplement Number
Cessna 172R, Nav III GFC 700 AFCS,
U.S. Pilot’s Operating Handbook
(Serials 17281497 and On)
FAA APPROVED
172RPHBUS-00
U.S.
9-1/9-2
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9
SUPPLEMENTS
LOG OF APPROVED SUPPLEMENTS
NOTE
IT IS THE AIRPLANE OWNER'S RESPONSIBILITY TO
MAKE SURE THAT HE OR SHE HAS THE LATEST
REVISION TO EACH SUPPLEMENT OF A PILOT'S
OPERATING HANDBOOK, AND THE LATEST ISSUED
"LOG OF APPROVED SUPPLEMENTS". THIS "LOG OF
A P P R O V E D S U P P L E M E N T S " WA S T H E L AT E S T
VERSION AS OF THE DATE IT WAS SHIPPED BY
CESSNA; HOWEVER, SOME CHANGES MAY HAVE
OCCURRED, AND THE OWNER SHOULD VERIFY THIS
IS THE LATEST, MOST UP-TO-DATE VERSION BY
C O N TA C T I N G C E S S N A P R O P E L L E R A I R C R A F T
CUSTOMER SERVICES AT (316) 517-5800.
Supplement
Name
Revision Equipment
Number
Level
Installed
1
Artex ME406 Emergency Locator
0
Transmitter (ELT)
2
Artex C406-N Emergency Locator
0
Transmitter (ELT)
3
Bendix/King KR87 Automatic
0
Direction Finder (ADF)
4
Winterization Kit
0
5
JAR-OPS Operational Eligibility
0
172RPHBUSLOG-00
20 December 2007
U.S.
Log 1/Log 2
CESSNA MODEL 172R
NAV III AVIONICS OPTION - GFC 700 AFCS
Serials 17281497 and On
SUPPLEMENT 1
ARTEX ME406
EMERGENCY LOCATOR TRANSMITTER (ELT)
SERIAL NO.
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Pilot's Operating Handbook
and FAA Approved Airplane Flight Manual when the Artex ME406 Emergency
Locator Transmitter (ELT) is installed.
COPYRIGHT © 2007
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
172RPHBUS-S1-00
20 DECEMBER 2007
U.S.
S1-1
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 1
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SUPPLEMENT 1
ARTEX ME406 EMERGENCY LOCATOR TRANSMITTER
(ELT)
Use the Log of Effective Pages to determine the current status of this
supplement.
Pages affected by the current revision are indicated by an asterisk (*)
preceding the page number.
Supplement Status
Original Issue
Date
20 December 2007
LOG OF EFFECTIVE PAGES
Page
Number
S1-1 thru S1-8
S1-2
U.S.
Page
Status
Revision
Number
Original
0
FAA APPROVED
172RPHBUS-S1-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 1
SERVICE BULLETIN CONFIGURATION LIST
The following is a list of Service Bulletins that are applicable to the
operation of the airplane, and have been incorporated into this
supplement. This list contains only those Service Bulletins that are
currently active.
Airplane Serial Revision
Number Title
FAA APPROVED
172RPHBUS-S1-00
Effectivity
Incorporated
Incorporated in Airplane
U.S.
S1-3
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 1
ARTEX
ME406
TRANSMITTER (ELT)
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
EMERGENCY
LOCATOR
GENERAL
The Artex ME406 Emergency Locator Transmitter (ELT) installation
uses a solid-state 2-frequency transmitter powered by an internal
lithium battery. The ME406 is also equipped with an instrument panelmounted remote switch assembly, that includes a red warning light, and
an external antenna mounted on the top of the tailcone. The remote
switch assembly is installed along the upper right instrument panel and
controls ELT operating modes from the flight crew station. When the
remote switch is set to the ARM position, the transmitter is energized
only when the internal "G” switch senses longitudinal inertia forces per
TSO-C91a/TSO-C126. When the remote switch is set to the ON
position, the transmitter is immediately energized.
The ME406 transmitter unit is located in the tailcone along the right
side behind the baggage compartment aft panel. On the ELT
transmitter unit is a panel containing an ARM/ON switch and a
transmitter warning light.
The ELT installation uses two different warnings to tell the pilot when
the ELT is energized. The aural warning is an unusual sound that is
easily heard by the pilot. The visual warning is a flashing red light
directly above the remote switch that shows the pilot that the ELT has
been activated.
When the ME406 is energized, the ELT transmits the standard swept
tone signal on the international VHF frequency of 121.5 MHz until
battery power is gone. The 121.5 MHz signal is mainly used to pinpoint
the beacon during search and rescue operations, and is monitored by
general aviation, commercial aircraft, and government agencies.
In addition, for the first 24 hours of the ELT being energized, a 406.028
MHz signal is transmitted at 50 second intervals. This transmission
lasts 440 milliseconds and contains identification data programmed into
the ELT and is received by COSPAS/SARSAT satellites. The
transmitted data may include the Aircraft ID, ELT Serial Number,
Country Code, and COSPAS/SARSAT ID.
(Continued Next Page)
S1-4
U.S.
FAA APPROVED
172RPHBUS-S1-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 1
ARTEX ME406 ELT CONTROL PANEL
1. ELT PANEL SWITCH (2-Position Toggle Switch):
a. ARM (OFF) - Turns OFF and ARMS transmitter for
automatic activation if “G” switch senses a predetermined
deceleration level.
b. ON - Activates transmitter instantly. The ON position
bypasses the automatic activation switch. The RED
warning light on ELT panel and on the remote switch
assembly mounted on the instrument panel should come
on.
2. TRANSMITTER WARNING LIGHT - Light comes on RED to
indicate the transmitter is transmitting a distress signal.
3. ANTENNA RECEPTACLE - Connects to the antenna mounted
on top of tailcone.
4. REMOTE CABLE JACK - Connects to the ELT remote switch
assembly located on the upper right instrument panel.
5. REMOTE SWITCH ASSEMBLY - (2-Position Rocker Switch):
a. ARM (OFF) - Turns OFF and ARMS transmitter for
automatic activation if “G” switch senses a predetermined
deceleration level.
b. ON - Remotely activates the transmitter for test or
emergency situations. The RED warning light above the
rocker switch comes on to indicate that the transmitter is
transmitting a distress signal.
Figure S1-1
FAA APPROVED
172RPHBUS-S1-00
U.S.
S1-5
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 1
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
OPERATING LIMITATIONS
There are no additional airplane operating limitations when the Artex
ME406 ELT is installed.
The airplane owner or operator must register the ME406 ELT with the
applicable civil aviation authority before use to make sure that the
identification code transmitted by the ELT is in the COSPAS/SARSAT
database. Refer to www.cospas-sarsat.org for registration information.
Refer to 14 CFR 91.207 for ELT inspection requirements. The ME406
must be inspected and tested by an approved technician using the
correct test equipment under the appropriate civil aviation authorities
approved conditions.
S1-6
U.S.
FAA APPROVED
172RPHBUS-S1-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 1
EMERGENCY PROCEDURES
If a forced landing is necessary, set the remote switch to the ON
position before landing. This is very important in remote or
mountainous terrain. The red warning light above the remote switch will
flash and the aural warning will be heard.
After a landing when search and rescue aid is needed, use the ELT as
follows:
NOTE
The ELT remote switch assembly could be inoperative if
damaged during a forced landing. If inoperative, the inertia
“G” switch will activate automatically. However, to turn the
ELT OFF and ON again requires manual switching of the
ELT panel switch which is located on the ELT unit.
1. MAKE SURE THE ELT IS ENERGIZED:
a. If the red warning light above the remote switch is not
flashing, set the remote switch to the ON position.
b. Listen for the aural warning. If the COM radio(s) operate and
can be energized safely (no threat of fire or explosion),
energize a COM radio and set the frequency to 121.5 MHz.
The ELT tone should be heard on the COM radio if the ELT
is working correctly. When done, de-energize the COM
radio(s) to conserve the airplane battery power.
c. Make sure that nothing is touching or blocking the ELT
antenna.
2. AFTER RESCUE - Set the remote switch to the ARM position to
de-energize the ELT. If the remote switch does not function, set
the switch on the ME406 (in the tailcone) to the ARM position.
FAA APPROVED
172RPHBUS-S1-00
U.S.
S1-7
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 1
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
NORMAL PROCEDURES
When operating in a remote area or over hazardous terrain, it is
recommended that the ELT be inspected by an approved technician
more frequently than required by 14 CFR 91.207.
NORMAL OPERATION
1. Check that the remote switch (on the upper right instrument
panel) is set to the ARM position.
Normal operation of the ME406 from the flight crew station is only to
de-energize and arm the ELT after it has been accidentally energized
(no emergency).
The ELT can be energized by a lightning strike or hard landing. If the
red light above the remote switch is flashing and the aural warning is
heard, the ELT is energized. Check for the emergency signal on a COM
radio set to 121.5 MHz. To stop the transmissions, set the remote
switch to the ON position momentarily and then set to the ARM
position. Tell the nearest Air Traffic Control facility about the accidental
transmissions as soon as possible to hold search and rescue work to a
minimum.
PERFORMANCE
There is no change to the airplane performance when the Artex ME406
ELT is installed.
S1-8
U.S.
FAA APPROVED
172RPHBUS-S1-00
CESSNA MODEL 172R
NAV III AVIONICS OPTION - GFC 700 AFCS
Serials 17281497 and On
SUPPLEMENT 2
ARTEX C406-N
EMERGENCY LOCATOR TRANSMITTER (ELT)
SERIAL NO.
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Pilot's Operating Handbook
and FAA Approved Airplane Flight Manual when the Artex C406-N Emergency
Locator Transmitter (ELT) is installed.
COPYRIGHT © 2007
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
172RPHBUS-S2-00
20 DECEMBER 2007
U.S.
S2-1
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 2
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SUPPLEMENT 2
ARTEX C406-N EMERGENCY LOCATOR TRANSMITTER
(ELT)
Use the Log of Effective Pages to determine the current status of this
supplement.
Pages affected by the current revision are indicated by an asterisk (*)
preceding the page number.
Supplement Status
Original Issue
Date
20 December 2007
LOG OF EFFECTIVE PAGES
Page
Number
S2-1 thru S2-8
S2-2
U.S.
Page
Status
Revision
Number
Original
0
FAA APPROVED
172RPHBUS-S2-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 2
SERVICE BULLETIN CONFIGURATION LIST
The following is a list of Service Bulletins that are applicable to the
operation of the airplane, and have been incorporated into this
supplement. This list contains only those Service Bulletins that are
currently active.
Airplane Serial Revision
Number Title
FAA APPROVED
172RPHBUS-S2-00
Effectivity
Incorporated
Incorporated in Airplane
U.S.
S2-3
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 2
ARTEX
C406-N
TRANSMITTER (ELT)
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
EMERGENCY
LOCATOR
GENERAL
The Artex C406-N Emergency Locator Transmitter (ELT) installation
uses a solid-state 3-frequency transmitter powered by an internal
lithium battery. The navigation function of the C406-N ELT receives
power from the airplane’s main battery thru Avionics Bus 1 and the
Essential Bus. The C406-N is also equipped with an instrument panelmounted remote switch assembly, that includes a red warning light, and
an external antenna mounted on the top of the tailcone. The remote
switch assembly is installed along the top right side of the instrument
panel and controls ELT operating modes from the flight crew station.
When the remote switch is set to the ARM position, the transmitter is
energized only when the internal "G-switch" senses longitudinal inertia
forces per TSO-C91a/TSO-C126. When the remote switch is set to the
ON position, the transmitter is immediately energized.
The C406-N transmitter unit is located in the tailcone along the right
side behind the baggage compartment aft panel. On the ELT
transmitter unit is a panel containing an ON/OFF switch and a
transmitter warning light.
The ELT installation uses two different warnings to tell the pilot when
the ELT is energized. The aural warning is an unusual sound that is
easily heard by the pilot. The visual warning is a flashing red light
directly above the remote switch that shows the pilot that the ELT has
been activated.
When the C406-N is energized, the ELT transmits the standard swept
tone signal on the international VHF frequency of 121.5 MHz and UHF
frequency of 243.0 MHz until battery power is gone. The 121.5 MHz
signal is mainly used to pinpoint the beacon during search and rescue
operations, and is monitored by general aviation, commercial aircraft,
and government agencies.
In addition, for the first 24 hours of the ELT being energized, a 406.028
MHz signal is transmitted at 50 second intervals. This transmission
lasts 440 milliseconds and contains identification data programmed into
the ELT and is received by COSPAS/SARSAT satellites. The
transmitted data may include the Aircraft ID, GPS coordinates, ELT
Serial Number, Country Code, and COSPAS/SARSAT ID.
(Continued Next Page)
S2-4
U.S.
FAA APPROVED
172RPHBUS-S2-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 2
ARTEX C406-N ELT CONTROL PANEL
1. ELT PANEL SWITCH (2-Position Toggle Switch):
a. OFF - Turns OFF and ARMS transmitter for automatic
activation if “G” switch senses a predetermined
deceleration level.
b. ON - Activates transmitter instantly. The ON position
bypasses the automatic activation switch. The RED
warning light on ELT panel and on the remote switch
assembly mounted on the instrument panel should come
on.
2. TRANSMITTER WARNING LIGHT - Light comes on RED to
indicate the transmitter is transmitting a distress signal.
3. REMOTE CABLE JACK - Connects to the ELT remote switch
assembly located on the upper right instrument panel.
4. ANTENNA RECEPTACLE - Connects to the antenna mounted
on top of tailcone.
5. REMOTE SWITCH ASSEMBLY - (2-Position Rocker Switch):
a. ARM (OFF) - Turns OFF and ARMS transmitter for
automatic activation if “G” switch senses a predetermined
deceleration level.
b. ON - Remotely activates the transmitter for test or
emergency situations. The RED warning light above the
rocker switch comes on to indicate that the transmitter is
transmitting a distress signal.
Figure S2-1
FAA APPROVED
172RPHBUS-S2-00
U.S.
S2-5
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 2
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
OPERATING LIMITATIONS
There are no additional airplane operating limitations when the Artex
C406-N ELT is installed.
The airplane owner or operator must register the C406-N ELT with the
applicable civil aviation authority before use to make sure that the
identification code transmitted by the ELT is in the COSPAS/SARSAT
database. Refer to www.cospas-sarsat.org for registration information.
Refer to 14 CFR 91.207 for ELT inspection requirements. The C406-N
must be inspected and tested by an approved technician using the
correct test equipment under the appropriate civil aviation authorities
approved conditions.
S2-6
U.S.
FAA APPROVED
172RPHBUS-S2-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 2
EMERGENCY PROCEDURES
If a forced landing is necessary, set the remote switch to the ON
position before landing. This is very important in remote or
mountainous terrain. The red warning light above the remote switch will
flash and the aural warning will be heard.
After a landing when search and rescue aid is needed, use the ELT as
follows:
NOTE
The ELT remote switch assembly could be inoperative if
damaged during a forced landing. If inoperative, the inertia
“G” switch will activate automatically. However, to turn the
ELT OFF and ON again requires manual switching of the
ELT panel switch which is located on the ELT unit.
1. MAKE SURE THE ELT IS ENERGIZED:
a. If the red warning light above the remote switch is not
flashing, set the remote switch to the ON position.
b. Listen for the aural warning. If the COM radio(s) operate and
can be energized safely (no threat of fire or explosion),
energize a COM radio and set the frequency to 121.5 MHz.
The ELT tone should be heard on the COM radio if the ELT
is working correctly. When done, de-energize the COM
radio(s) to conserve the airplane battery power.
c. Make sure that nothing is touching or blocking the ELT
antenna.
2. AFTER RESCUE - Set the remote switch to the ARM position to
de-energize the ELT. If the remote switch does not function, set
the switch on the C406-N (in the tailcone) to the OFF position.
FAA APPROVED
172RPHBUS-S2-00
U.S.
S2-7
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 2
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
NORMAL PROCEDURES
When operating in a remote area or over hazardous terrain, it is
recommended that the ELT be inspected by an approved technician
more frequently than required by 14 CFR 91.207.
NORMAL OPERATION
1. Check that the remote switch (on the right instrument panel) is
set to the ARM position.
Normal operation of the C406-N from the flight crew station is only to
de-energize and arm the ELT after it has been accidentally energized
(no emergency).
The ELT can be energized by a lightning strike or hard landing. If the
red light above the remote switch is flashing and the aural warning is
heard, the ELT is energized. Check for the emergency signal on a COM
radio set to 121.5 MHz. To stop the transmissions, set the remote
switch to the ON position momentarily and then set to the ARM
position. Tell the nearest Air Traffic Control facility about the accidental
transmissions as soon as possible to hold search and rescue work to a
minimum.
PERFORMANCE
There is no change to the airplane performance when the Artex C406-N
ELT is installed.
S2-8
U.S.
FAA APPROVED
172RPHBUS-S2-00
CESSNA MODEL 172R
NAV III AVIONICS OPTION - GFC 700 AFCS
Serials 17281497 and On
SUPPLEMENT 3
BENDIX/KING KR87
AUTOMATIC DIRECTION FINDER (ADF)
SERIAL NO.
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Pilot's Operating Handbook
and FAA Approved Airplane Flight Manual when the Bendix/King KR 87 Automatic
Direction Finder (ADF) is installed.
COPYRIGHT © 2007
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
172RPHBUS-S3-00
20 DECEMBER 2007
U.S.
S3-1
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SUPPLEMENT 3
BENDIX/KING
FINDER (ADF)
KR87
AUTOMATIC
DIRECTION
Use the Log of Effective Pages to determine the current status of this
supplement.
Pages affected by the current revision are indicated by an asterisk (*)
preceding the page number.
Supplement Status
Original Issue
Date
20 December 2007
LOG OF EFFECTIVE PAGES
Page
Number
S3-1 thru S3-12
S3-2
U.S.
Page
Status
Revision
Number
Original
0
FAA APPROVED
172RPHBUS-S3-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
SERVICE BULLETIN CONFIGURATION LIST
The following is a list of Service Bulletins that are applicable to the
operation of the airplane, and have been incorporated into this
supplement. This list contains only those Service Bulletins that are
currently active.
Number
Title
FAA APPROVED
172RPHBUS-S3-00
Airplane Serial Revision
Effectivity
Incorporated
U.S.
Incorporated
in Airplane
S3-3
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
BENDIX/KING
FINDER (ADF)
KR87
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
AUTOMATIC
DIRECTION
GENERAL
The Bendix/King Digital ADF is a panel-mounted, digitally tuned
automatic direction finder. It is designed to provide continuous 1-kHz
digital tuning in the frequency range of 200-kHz to 1799-kHz and
eliminates the need for mechanical band switching. The system has a
receiver, a built-in electronic timer, a bearing pointer shown on the
G1000 Horizontal Situation Indicator (HSI), and a KA-44B combined
loop and sense antenna. Controls and displays for the Bendix/King
Digital ADF are shown and described in Figure S3-1. The Garmin GMA
1347 Audio Panel is used to control audio output. Audio panel
operation is described in the Garmin G1000 Cockpit Reference Guide.
The Bendix/King Digital ADF can be used for position plotting and
homing procedures, and for aural reception of amplitude modulated
(AM) signals.
The flip-flop frequency display allows switching between preselected
standby and active frequencies by pushing the frequency transfer
button. Both preselected frequencies are stored in a nonvolatile
memory circuit (no battery power required) and displayed in large,
easy-to-read, self-dimming gas discharge numbers. The active
frequency is continuously displayed in the left window, while the right
window will display either the standby frequency or the selected
readout from the built-in electronic timer.
The built-in electronic timer has two timing functions that operate
independently. An automatic flight timer starts when the unit is turned
on. This timer counts up to 59 hours and 59 minutes. An elapsed timer
will count up or down for up to 59 minutes and 59 seconds. When a
preset time interval has been programmed and the countdown reaches
:00, the display will flash for 15 seconds. Since both the flight timer and
elapsed timer operate independently, it is possible to monitor either one
without disrupting the other. The pushbutton controls are internally
lighted. The light intensity is controlled by the AVIONICS dimmer
control.
(Continued Next Page)
S3-4
U.S.
FAA APPROVED
172RPHBUS-S3-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
BENDIX/KING KR87 AUTOMATIC DIRECTION
FINDER (ADF)
Figure S3-1
FAA APPROVED
172RPHBUS-S3-00
U.S.
S3-5
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
GENERAL (Continued)
1. ANT/ADF MODE ANNUNCIATOR - Antenna (ANT) is selected
when the ADF button is in the OUT position. This mode
improves the audio reception and is usually used for station
identification. The bearing pointer is deactivated and will park in
the 90° relative position. Automatic Direction Finder (ADF) mode
is selected by pushing the ADF button. This mode activates the
bearing pointer and will point in the direction of the station
relative to the aircraft heading.
2. ACTIVE FREQUENCY DISPLAY - The frequency to which the
ADF is tuned is displayed here. The active ADF frequency can
be changed directly when either of the timer functions is
selected.
3. BFO (Beat Frequency Oscillator) ANNUNCIATOR - The BFO
mode is activated and annunciated by pushing the BFO button.
When BFO mode is active, the carrier wave and its morse code
identifier can be heard.
NOTE
CW signals (Morse Code) are unmodulated and no audio
will be heard without use of BFO. This type of signal is not
used in the United States air navigation. It is used in some
foreign countries and marine beacons.
4. STANDBY FREQUENCY/FLIGHT TIME OR ELAPSED TIME
DISPLAY - When FRQ is shown, the STANDBY frequency is
shown in the right display. The STANDBY frequency is selected
using the frequency select knobs. The selected STANDBY
frequency is put into the active frequency window by pushing the
frequency transfer button. Either the standby frequency, the
flight timer, or the elapsed time is shown in this position. The
flight timer and elapsed timer replace the standby frequency
which goes into blind memory to be called back at any time by
pushing the FRQ button. Flight time or elapsed time are shown
and annunciated by depressing the FLT/ET button.
5. FLIGHT
TIMER
AND
ELAPSED
TIMER
MODE
ANNUNCIATION - Either the elapsed time (ET) or flight time
(FLT) mode is annunciated here.
(Continued Next Page)
S3-6
U.S.
FAA APPROVED
172RPHBUS-S3-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
GENERAL (Continued)
6. FREQUENCY SELECT KNOBS - Selects the standby frequency
when FRQ is displayed and directly selects the active frequency
whenever either of the time functions is selected. The frequency
selector knobs may be turned either clockwise or
counterclockwise. The small knob is pulled out to tune the 1's.
The small knob is pushed in to tune the 10's. The outer knob
tunes the 100's with rollover into the 1000's up to 1799. These
knobs are also used to set the desired time when the elapsed
timer is used in the countdown mode.
7. ON/OFF/VOLUME CONTROL SWITCH (ON/OFF/VOL) Controls power and audio output level. Turn the control switch
clockwise from the OFF position to energize the receiver and
increase audio volume. The KR87 has audio muting which
causes the audio output to be muted unless the receiver is
locked on a valid station.
8. SET/RESET ELAPSED TIMER BUTTON (SET/RST) - The SET/
RST button resets the elapsed timer whether it is being
displayed or not.
9. FLIGHT TIMER/ELAPSED TIMER MODE SELECTOR
BUTTON (FLT/ET) - The FLT/ET button selects either Flight
Timer mode or Elapsed Timer mode when pushed.
10. FREQUENCY TRANSFER BUTTON (FRQ) - The FRQ transfer
button interchanges the active and standby frequencies when
pushed.
11. BFO (Beat Frequency Oscillator) BUTTON - The BFO button
selects the BFO mode when pushed in. (See note under item 3).
12. ADF BUTTON - The ADF button selects either the ANT mode or
the ADF mode. The ANT mode is selected when the ADF button
is in the out position. The ADF mode is selected when the ADF
button is pushed in.
13. LUBBER LINE - Indicates magnetic heading of the airplane.
14. ROTATING COMPASS ROSE (HSI COMPASS CARD) - The
rotating compass rose turns as the heading of the airplane
changes. The magnetic heading of the airplane is under the
lubber line.
15. BEARING POINTER - Shows magnetic bearing to the station.
16. BEARING INFORMATION WINDOW - Shows the type of
pointer that is being used as the ADF bearing pointer. If ADF is
not shown, push the BRG1 or BRG2 softkey until ADF is shown.
FAA APPROVED
172RPHBUS-S3-00
U.S.
S3-7
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
OPERATING LIMITATIONS
Refer to Section 2 of the Pilot's Operating Handbook and FAA
Approved Flight Manual (POH/AFM).
EMERGENCY PROCEDURES
There is no change to the airplane emergency procedures when the
Bendix/King KR 87 Automatic Direction Finder (ADF) is installed.
NORMAL PROCEDURES
TO OPERATE AS AN AUTOMATIC DIRECTION FINDER:
1. OFF/VOL Control - ON
2. Frequency Selector Knobs - SELECT desired frequency in the
standby frequency display.
3. FRQ Button - PUSH to move the desired frequency from the
standby to the active position.
4. ADF Selector Switch (on audio control panel) - SELECT as
desired.
5. OFF/VOL Control - SET to desired volume level and identify that
desired station is being received.
6. PFD Softkey (on PFD) - PUSH to show BRG1 and BRG2
softkeys.
7. BRG1 or BRG2 Softkey (on PFD) - PUSH to show ADF in
Bearing Information Window.
8. ADF Button - SELECT ADF mode and note magnetic bearing on
HSI.
(Continued Next Page)
S3-8
U.S.
FAA APPROVED
172RPHBUS-S3-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
NORMAL PROCEDURES (Continued)
ADF TEST (PREFLIGHT or IN FLIGHT):
1. ADF Button - SELECT ANT mode and note pointer moves to
90° position.
2. ADF Button - SELECT ADF mode and note the pointer moves
without hesitation to the station bearing. Excessive pointer
sluggishness, wavering or reversals indicate a signal that is too
weak or a system malfunction.
TO OPERATE BFO:
1. OFF/VOL Control - ON
2. BFO Button - PRESS ON
3. ADF Selector Buttons (on audio control panel) - SET to desired
mode.
4. VOL Control - ADJUST to desired listening level.
NOTE
A 1000-Hz tone and Morse Code identifier is heard in the
audio output when a CW signal is received.
TO OPERATE FLIGHT TIMER:
1. OFF/VOL Control - ON
2. FLT/ET Mode Button - PRESS (once or twice) until FLT is
annunciated. Timer will already be counting since it is activated
by turning the unit on.
3. OFF/VOL Control - OFF and then ON if it is desired to reset the
flight timer.
TO OPERATE AS A COMMUNICATIONS RECEIVER ONLY:
1. OFF/VOL Control - ON
2. ADF Button - SELECT ANT mode
3. Frequency Selector Knobs - SELECT desired frequency in the
standby frequency display.
4. FRQ Button - PRESS to move the desired frequency from the
standby to the active position.
5. ADF Selector Buttons (on audio control panel) - SET to desired
mode.
6. VOL Control - ADJUST to desired listening level.
(Continued Next Page)
FAA APPROVED
172RPHBUS-S3-00
U.S.
S3-9
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
NORMAL PROCEDURES (Continued)
TO OPERATE ELAPSED TIME TIMER-COUNT UP MODE:
1. OFF/VOL Control - ON
2. FLT/ET Mode Button - PRESS (once or twice) until ET is
annunciated.
3. SET/RST Button - PRESS momentarily to reset elapsed timer to
zero.
NOTE
The Standby Frequency which is in memory while Flight
Time or Elapsed Time modes are being displayed may be
called back by pushing the FRQ button, then transferred to
active by pushing the FRQ button again.
TO OPERATE ELAPSED TIME TIMER COUNT DOWN
MODE:
1. OFF/VOL Control - ON
2. FLT/ET Mode Button - PRESS (once or twice) until ET is
annunciated.
3. SET/RST Button - PRESS until the ET annunciation begins to
flash.
4. FREQUENCY SELECTOR KNOBS - SET desired time in the
elapsed time display. The small knob is pulled out to tune the
1's. The small knob is pushed in to tune the 10's. The outer knob
tunes minutes up to 59 minutes.
NOTE
Selector knobs remain in the time set mode for 15 seconds
after the last entry or until the SET/RST, FLT/ET or FRQ
button is pressed.
(Continued Next Page)
S3-10
U.S.
FAA APPROVED
172RPHBUS-S3-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
NORMAL PROCEDURES (Continued)
TO OPERATE ELAPSED TIME TIMER COUNT DOWN
MODE: (Continued)
5. SET/RST Button - PRESS to start countdown. When the timer
reaches 0, it will start to count up as display flashes for 15
seconds.
NOTE
While FLT or ET are displayed, the active frequency on the
left side of the window may be changed, by using the
frequency selector knobs, without any effect on the stored
standby frequency or the other modes.
ADF OPERATION NOTES:
ERRONEOUS ADF BEARING DUE TO RADIO FREQUENCY
PHENOMENA:
In the U.S., the FCC, which assigns AM radio frequencies, occasionally
will assign the same frequency to more than one station in an area.
Certain conditions, such as Night Effect, may cause signals from such
stations to overlap. This should be taken into consideration when using
AM broadcast stations for navigation.
Sunspots and atmospheric phenomena may occasionally distort
reception so that signals from two stations on the same frequency will
overlap. For this reason, it is always wise to make positive identification
of the station being tuned, by switching the function selector to ANT
and listening for station call letters.
In the vicinity of electrical storms, an ADF indicator pointer tends to
swing from the station tuned toward the center of the storm.
(Continued Next Page)
FAA APPROVED
172RPHBUS-S3-00
U.S.
S3-11
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 3
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
NORMAL PROCEDURES (Continued)
ADF OPERATION NOTES: (Continued)
ELECTRICAL STORMS:
In the vicinity of electrical storms, an ADF indicator pointer tends to
swing from the station tuned toward the center of the storm.
NIGHT EFFECT:
This is a disturbance particularly strong just after sunset and just after
dawn. An ADF indicator pointer may swing erratically at these times. If
possible, tune to the most powerful station at the lowest frequency. If
this is not possible, take the average of pointer oscillations to determine
station bearing.
MOUNTAIN EFFECT:
Radio waves reflecting from the surface of mountains may cause the
pointer to fluctuate or show an erroneous bearing. This should be taken
into account when taking bearings over mountainous terrain.
COASTAL REFRACTION:
Radio waves may be refracted when passing from land to sea or when
moving parallel to the coastline. This also should be taken into account.
PERFORMANCE
There is no change in airplane performance when the Bendix/King KR
87 Automatic Direction Finder (ADF) is installed. However, the
installation of an externally mounted antenna or related external
antennas, will result in a minor reduction in cruise performance.
S3-12
U.S.
FAA APPROVED
172RPHBUS-S3-00
CESSNA MODEL 172R
NAV III AVIONICS OPTION - GFC 700 AFCS
Serials 17281497 and On
SUPPLEMENT 4
WINTERIZATION KIT
SERIAL NO.
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Pilot's Operating Handbook
and FAA Approved Airplane Flight Manual when the Winterization Kit is installed.
COPYRIGHT © 2007
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
172RPHBUS-S4-00
20 DECEMBER 2007
U.S.
S4-1
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 4
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SUPPLEMENT 4
WINTERIZATION KIT
Use the Log of Effective Pages to determine the current status of this
supplement.
Pages affected by the current revision are indicated by an asterisk (*)
preceding the page number.
Supplement Status
Date
Original Issue
20 December 2007
LOG OF EFFECTIVE PAGES
Page
Number
S4-1 thru S4-6
S4-2
U.S.
Page
Status
Revision
Number
Original
0
FAA APPROVED
172RPHBUS-S4-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 4
SERVICE BULLETIN CONFIGURATION LIST
The following is a list of Service Bulletins that are applicable to the
operation of the airplane, and have been incorporated into this
supplement. This list contains only those Service Bulletins that are
currently active.
Number
Title
FAA APPROVED
172RPHBUS-S4-00
Airplane Serial Revision
Effectivity
Incorporated
U.S.
Incorporated
in Airplane
S4-3
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 4
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
WINTERIZATION KIT
GENERAL
The winterization kit consists of two cover plates, with placards, which
attach to the air intakes in the cowling nose cap, a placard silk
screened on the instrument panel, and insulation for the crankcase
breather tube. This equipment should be installed for operations in
temperatures consistently below 20°F (-7°C). Once installed, the
crankcase breather insulation is approved for permanent use in both
hot and cold weather operations.
Figure S4-1
S4-4
U.S.
FAA APPROVED
172RPHBUS-S4-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 4
OPERATING LIMITATIONS
The following information must be presented in the form of placards
when the airplane is equipped with a winterization kit.
1. On each nose cap cover plate:
2. On the instrument panel below the PFD:
FAA APPROVED
172RPHBUS-S4-00
U.S.
S4-5
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 4
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
EMERGENCY PROCEDURES
There is no change to the airplane emergency procedures when the
winterization kit is installed.
NORMAL PROCEDURES
There is no change to the airplane normal procedures when the
winterization kit is installed.
PERFORMANCE
There is no change to the airplane performance when the winterization
kit is installed.
S4-6
U.S.
FAA APPROVED
172RPHBUS-S4-00
CESSNA MODEL 172R
NAV III AVIONICS OPTION - GFC 700 AFCS
Serials 17281497 and On
SUPPLEMENT 5
JAR-OPS OPERATIONAL ELIGIBILITY
SERIAL NO.
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Pilot's Operating Handbook
and FAA Approved Airplane Flight Manual for JAR-OPS Operational Eligibility.
COPYRIGHT © 2007
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
172RPHBUS-S5-00
20 DECEMBER 2007
U.S.
S5-1
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 5
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SUPPLEMENT 5
JAR-OPS OPERATIONAL ELIGIBILITY
Use the Log of Effective Pages to determine the current status of this
supplement.
Pages affected by the current revision are indicated by an asterisk (*)
preceding the page number.
Supplement Status
Date
Original Issue
20 December 2007
LOG OF EFFECTIVE PAGES
Page
Number
S5-1 thru S5-5/S5-6
S5-2
U.S.
Page
Status
Revision
Number
Original
0
FAA APPROVED
172RPHBUS-S5-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 5
SERVICE BULLETIN CONFIGURATION LIST
The following is a list of Service Bulletins that are applicable to the
operation of the airplane, and have been incorporated into this
supplement. This list contains only those Service Bulletins that are
currently active.
Number
Title
FAA APPROVED
172RPHBUS-S5-00
Airplane Serial Revision
Effectivity
Incorporated
U.S.
Incorporated
in Airplane
S5-3
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 5
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
JAR-OPS OPERATIONAL ELIGIBILITY
GENERAL
OPERATIONAL ELIGIBILITY
The JAA TGLs noted below specify that Operational Eligibility
information be included in the airplane POH/AFM or POH/AFM
Supplement for convenience in the JAR-OPS approval process. This
Supplement provides a consistent location for the requested
information. This information does not address the operation of the
airplane or equipment by the pilot.
NAVIGATION OPERATIONAL ELIGIBILITY
The GPS/GNSS receivers in the G1000 System are certified to TSO
C129a Class A1 and ETSO C129a Class A1 or TSO C145a and ETSO
2C145a.
The installed performance of the G1000 System has been tested and
approved for IFR enroute, terminal and non-precision (RNAV or GPS)
approach operations per AC 20-138A when using GPS/GNSS with the
correct navigation database.
The G1000 System meets the requirements for GPS/GNSS as a
Primary Means of Navigation for Oceanic/Remote Operations (RNP10) per AC 20-138A, FAA Notice N8110.60, FAA Order 8400-12A and
FAA Order 8700-1. Both GPS/GNSS receivers are required to be
operating and receiving usable signals except for routes requiring only
one Long Range Navigation sensor.
The G1000 System has been shown to be eligible for BRNAV (RNP-5)
and PRNAV (RNP-1) Enroute and Terminal navigation per JAA TGL-2
(ACJ20X4), JAA TGL-10 and AC 90-96A provided that the G1000 is
receiving usable navigation information from at least one GPS receiver.
Eligibility does not constitute Operational Approval.
(Continued Next Page)
S5-4
U.S.
FAA APPROVED
172RPHBUS-S5-00
CESSNA
MODEL 172R NAV III
GFC 700 AFCS
SECTION 9 - SUPPLEMENTS
SUPPLEMENT 5
GENERAL (Continued)
SSR
MODE
S
ENHANCED
OPERATIONAL ELIGIBILITY
SURVEILLANCE
The GTX 33 Transponder is certified to TSO C112a and ETSO 2C112a.
The installed performance of the GTX 33 has been tested and
approved per AC 20-131A, Draft AC-131B and AC 23-8B.
The GTX 33 is able to respond to interrogations in Modes A, C and is
fully compliant with the requirements of Mode S Elementary
Surveillance per TGL 13 Rev 1 and Draft TGL 13 Rev 2. Extended
Squitter functionality is supported by the GTX 33. This does not
constitute airworthiness or operational approval for Extended Squitter
functionality.
OPERATING LIMITATIONS
There is no change to the airplane operating limitations for JAR-OPS
Operational Eligibility. JAR-OPS may require separate airspace
operating limitations.
EMERGENCY PROCEDURES
There is no change to the airplane emergency procedures for JAROPS Operational Eligibility.
NORMAL PROCEDURES
There is no change to the airplane normal procedures for JAR-OPS
Operational Eligibility.
PERFORMANCE
There is no change to the airplane performance for JAR-OPS
Operational Eligibility.
FAA APPROVED
172RPHBUS-S5-00
U.S.
S5-5/S5-6
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