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CESSNA INTRODUCTION

MODEL 172R NAV III

GFC 700 AFCS

U.S.

NOTICE

AT THE TIME OF ISSUANCE, THIS INFORMATION

MANUAL WAS AN EXACT DUPLICATE OF THE

OFFICIAL PILOT’S OPERATING HANDBOOK AND

FAA APPROVED AIRPLANE FLIGHT MANUAL AND

IS TO BE USED FOR GENERAL PURPOSES ONLY.

IT WILL NOT BE KEPT CURRENT AND,

THEREFORE, CANNOT BE USED AS A

SUBSTITUTE FOR THE OFFICIAL PILOT’S

OPERATING HANDBOOK AND FAA APPROVED

AIRPLANE FLIGHT MANUAL INTENDED FOR

OPERATION OF THE AIRPLANE.

THE PILOT’S OPERATING HANDBOOK MUST BE

CARRIED IN THE AIRPLANE AND AVAILABLE TO

THE PILOT AT ALL TIMES.

Cessna Aircraft Company

Original Issue - 20 December 2007

iOriginal Issue

Summary of content (350 pages)

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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.
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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 . . . . . . . . . . . . . . . . . . .
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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.
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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.
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CESSNA MODEL 172R NAV III GFC 700 AFCS INTRODUCTION TABLE OF CONTENTS SECTION GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 LIMITATIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 PERFORMANCE . . . . . . . . . . . . . . . . . . . . . . .
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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 . . . . . . . .
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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.
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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.
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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.
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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.
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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.
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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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).
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CESSNA MODEL 172R NAV III GFC 700 AFCS SECTION 1 GENERAL WEIGHT CONVERSIONS Figure 1-2 (Sheet 1 of 2) 172RPHBUS-00 U.S.
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SECTION 1 GENERAL CESSNA MODEL 172R NAV III GFC 700 AFCS WEIGHT CONVERSIONS Figure 1-2 (Sheet 2) 1-18 U.S.
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CESSNA MODEL 172R NAV III GFC 700 AFCS SECTION 1 GENERAL LENGTH CONVERSIONS Figure 1-3 (Sheet 1 of 4) 172RPHBUS-00 U.S.
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SECTION 1 GENERAL CESSNA MODEL 172R NAV III GFC 700 AFCS LENGTH CONVERSIONS Figure 1-3 (Sheet 2) 1-20 U.S.
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CESSNA MODEL 172R NAV III GFC 700 AFCS SECTION 1 GENERAL LENGTH CONVERSIONS Figure 1-3 (Sheet 3) 172RPHBUS-00 U.S.
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SECTION 1 GENERAL CESSNA MODEL 172R NAV III GFC 700 AFCS LENGTH CONVERSIONS Figure 1-3 (Sheet 4) 1-22 U.S.
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CESSNA MODEL 172R NAV III GFC 700 AFCS SECTION 1 GENERAL DISTANCE CONVERSIONS Figure 1-4 172RPHBUS-00 U.S.
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SECTION 1 GENERAL CESSNA MODEL 172R NAV III GFC 700 AFCS VOLUME CONVERSIONS Figure 1-5 (Sheet 1 of 3) 1-24 U.S.
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CESSNA MODEL 172R NAV III GFC 700 AFCS SECTION 1 GENERAL VOLUME CONVERSIONS Figure 1-5 (Sheet 2) 172RPHBUS-00 U.S.
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SECTION 1 GENERAL CESSNA MODEL 172R NAV III GFC 700 AFCS VOLUME CONVERSIONS Figure 1-5 (Sheet 3) 1-26 U.S.
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CESSNA MODEL 172R NAV III GFC 700 AFCS SECTION 1 GENERAL TEMPERATURE CONVERSIONS Figure 1-6 172RPHBUS-00 U.S.
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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.
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CESSNA MODEL 172R NAV III GFC 700 AFCS SECTION 1 GENERAL VOLUME TO WEIGHT CONVERSION Figure 1-8 172RPHBUS-00 U.S.
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SECTION 1 GENERAL CESSNA MODEL 172R NAV III GFC 700 AFCS QUICK CONVERSIONS Figure 1-9 1-30 U.S.
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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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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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.
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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.
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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.
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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: . . .
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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.
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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 . . . . . . . . . . . . . . . . . . . . . . . .
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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.
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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. . . . . . . .
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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.
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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.
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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
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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 Sourc
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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 Interna
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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 At
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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
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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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 . . . . . . . . . . . . . . . . .
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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL 172R NAV III GFC 700 AFCS MAXIMUM GLIDE Figure 3-1 3-26 U.S.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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. . . . . . . . .
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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. . . . . . . . . . . . . . . . . . . . . .
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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 . . . . . . . . . . . . . . . . . . . . . . . . . .
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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 .
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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).
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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 . . .
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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 CL
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SECTION 5 PERFORMANCE CESSNA MODEL 172R NAV III GFC 700 AFCS TEMPERATURE CONVERSION CHART Figure 5-2 5-12 U.S.
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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 4
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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 Le
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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 . . . . . . . . . . . . . . . . . . . . . .
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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).
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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
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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
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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.
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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
PAGE 199
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.
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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
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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 . . . . . . . . . . . . . . . . . . . . . .
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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. . . . . . . . . . . . . . . . . . . . . .
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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 . . . . . . . . . . . . .
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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SECTION 7 AIRPLANE AND SYSTEM DESCRIPTION CESSNA MODEL 172R NAV III GFC 700 AFCS INSTRUMENT PANEL Figure 7-2 7-14 U.S.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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SECTION 7 AIRPLANE AND SYSTEM DESCRIPTION CESSNA MODEL 172R NAV III GFC 700 AFCS FUEL SYSTEM (Continued) Figure 7-6 7-42 U.S.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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CESSNA 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.
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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.
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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.
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SECTION 7 AIRPLANE AND SYSTEM DESCRIPTION CESSNA MODEL 172R NAV III GFC 700 AFCS VACUUM SYSTEM Figure 7-9 7-66 U.S.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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CESSNA 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.
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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.
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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 . . . . . . . . . .
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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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: . . . . . . . . . . . .
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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".
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
PAGE 342
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).
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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.
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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.
PAGE 345
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.
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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.
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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.
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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.
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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.
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