Cessna 177 Pilot's Operating Handbook

6'-4" MAX. NOTES: 11'-10" 1. 35' 8'-3½" Wing span shown with strobe lights installed. Maximum height shown with 2. nose gear depressed and all tires and nose strut properly inflated. 3. Wheel base length is 76%". 4. Propeller ground clearance is 8 1/8". 5. Wing area is 174 square feet. 6. Minimum turning radius (*pivot point to outboard wing tip) is 25'6". * PIVOT POINT Figure 1-1. Three View DESCRIPTIVE DATA ENGINE Number of Engines: 1. Engine Manufacturer: Avco Lycoming. Engine Model Number: 0-360-A1F6D. Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally- opposed, carburetor equipped, four-cylinder engine with 361 cu. in. displacement. Horsepower Rating and Engine Speed: 180 rated BHP at 2700 RPM. PROPELLER Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: B2D34C211/82PCA-6. Number of Blades: 2. Propeller Diameter, Maximum: 76 inches. Minimum: 75 inches. Propeller Type: Constant speed and hydraulically actuated, with a low pitch setting of 12.1° and a high pitch setting of 26.0° (30 inch station). FUEL Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). Fuel Capacity: Standard Tanks: Total Capacity: 50 gallons. Total Capacity Each Tank: 25 gallons. Total Usable: 49 gallons. 1-3 SECTION 1 GENERAL OIL CESSNA MODEL 177B Long Range Tanks: Total Capacity: 61 gallons. Total Capacity Each Tank: 30.5 gallons. Total Usable: 60 gallons. NOTE To ensure maximum fuel capacity when refueling, place the fuel selector valve in either LEFT or RIGHT posi- tion to prevent cross-feeding. CESSNA MODEL 177B SECTION 1 GENERAL Landing, Normal Category: 2500 lbs. Utility Category: 2200 lbs. Weight in Baggage Compartment, Normal Category: Baggage, passenger on auxiliary seat, or cargo area 2 and hatshelf Station 142 to 185: 120 lbs. - NOTE The maximum combined weight capacity for cargo area 2 and the hatshelf is 120 lbs. The maximum weight capacity for the hatshelf is 25 lbs. Weight in Baggage Compartment, Utility Category: In this category, the baggage compartment and rear seat must not be occupied. Oil Grade (Specification): MIL-L-6082 Aviation Grade Straight Mineral Oil: Use to replenish supply during first 25 hours and at the first 25-hour oil change. Continue to use until a total of 50 hours has accumulated or oil consumption has stabilized. NOTE The airplane was delivered from the factory with a corro- sion preventive aircraft engine oil. This oil should be drained after the first 25 hours of operation. MIL-L-22851 Ashless Dispersant Oil: This oil must be used after first 50 hours or oil consumption has stabilized. Recommended Viscosity For Temperature Range: MIL-L-6082 Aviation Grade Straight Mineral Oil: SAE 50 above 16°C (60°F). SAE 40 between -1°C (30°F) and 32°C (90°F). SAE 30 between -18°C (0°F) and 21°C (70°F). SAE 20 below -12°C (10°F). MIL-L-22851 Ashless Dispersant Oil: SAE 40 or SAE 50 above 16°C (60°F). SAE 40 between -1°C (30°F) and 32°C (90°F). SAE 30 or SAE 40 between -18°C (0°F) and 21°C (70°F). SAE 30 below -12°C (10°F). Oil Capacity: Sump: 8 Quarts. Total: 9 Quarts. MAXIMUM CERTIFICATED WEIGHTS Takeoff, Normal Category: 2500 lbs. Utility Category: 2200 lbs. STANDARD AIRPLANE WEIGHTS 1533 lbs. Cardinal II: 1560 lbs. Standard Empty Weight, Cardinal: Maximum Useful Load: Cardinal: Cardinal II: Normal Category 967 lbs. 940 lbs. Utility Category 667 lbs. 640 lbs. CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6. BAGGAGE SPACE AND ENTRY DIMENSIONS Dimensions of the baggage area and baggage door opening are illus- trated in detail in Section 6. SPECIFIC LOADINGS Power Loading: 13.9 lbs./hp. Wing Loading: 14.4 lbs./sq. ft. 1-4 1-5 SECTION 1 GENERAL CESSNA MODEL 177B SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS VA VFE VNO 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 at- mosphere at sea level. Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots. Knots True Airspeed is the airspeed expressed in knots rel- ative to undisturbed air which is KCAS corrected for altitude and temperature. Maneuvering Speed is the maximum speed at which you may use abrupt control travel. Maximum Flap Extended Speed is the highest speed permis- sible with wing flaps in a prescribed extended position. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, then only with caution. CESSNA MODEL 177B SECTION 1 GENERAL Standard Temperature is 15°C at sea level pressure altitude and decreases by 2°C for each 1000 feet of altitude. Standard Tempera- ture Pressure Altitude Pressure Altitude is the altitude read from an altimeter when the altimeter's barometric scale has been set to 29.92 inches of mercury (1013 mb). ENGINE POWER TERMINOLOGY BHP RPM Brake Horsepower is the power developed by the engine. Revolutions Per Minute is engine speed. MP Manifold Pressure is a pressure measured in the engine's induction system and is expressed in inches of mercury (Hg). AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demonstrated Crosswind Velocity is the velocity of the cross- wind 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. Demon- strated Crosswind Velocity Usable Fuel Usable Fuel is the fuel available for flight planning. V. NE Never Exceed Speed is the speed limit that may not be exceeded at any time. Unusable Stalling Speed or the minimum steady flight speed at which the airplane is controllable. Fuel GPH Vs 5 VSO Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration at the most forward center of gravity. NMPG Vx Best Angle-of-Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance. g Best Rate-of-Climb Speed is the speed which results in the greatest gain in altitude in a given time. Vy METEOROLOGICAL TERMINOLOGY Unusable Fuel is the quantity of fuel that can not be safely used in flight. Gallons Per Hour is the amount of fuel (in gallons) consumed per hour. Nautical Miles Per Gallon is the distance (in nautical miles) which can be expected per gallon of fuel consumed at a spe- cific engine power setting and/or flight configuration. g is acceleration due to gravity. WEIGHT AND BALANCE TERMINOLOGY Reference Datum OAT Outside Air Temperature is the free air static temperature. It is expressed in either degrees Celsius (formerly Centi- grade) or degrees Fahrenheit. Station Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. Station is a location along the airplane fuselage given in terms of the distance from the reference datum. 1-6 1-7 SECTION 1 GENERAL Arm Moment Center of Gravity (C. G.) C. G. Arm C.G. Limits Standard Empty Weight CESSNA MODEL 177B. Arm is the horizontal distance from the reference datum to the center of gravity (C. G.) of an item. Moment is the product of the weight of an item multiplied by its arm. (Moment divided by the constant 1000 is used in this handbook to simplify balance calculations by reducing the number of digits.) Center of Gravity is the point at which an airplane, or equip- ment, would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. Center of Gravity Arm is the arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight. Standard Empty Weight is the weight of a standard airplane, including unusable fuel, full operating fluids and full engine oil. Basic Empty Basic Empty Weight is the standard empty weight plus the Weight weight of optional equipment. Useful Load Gross (Loaded) Weight Maximum Takeoff Weight Maximum Landing Weight Tare 1-8 Useful Load is the difference between takeoff weight and the basic empty weight. Gross (Loaded) Weight is the loaded weight of the airplane. Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff run. Maximum Landing Weight is the maximum weight approved for the landing touchdown. Tare is the weight of chocks, blocks, stands, etc. used when weighing an airplane, and is included in the scale readings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. CESSNA MODEL 177B SECTION 2 LIMITATIONS TABLE OF CONTENTS Introduction Airspeed Limitations Normal Category . Utility Category SECTION 2 LIMITATIONS Page 2-3 2-4 Airspeed Indicator Markings 2-4 Power Plant Limitations 2-5 Power Plant Instrument Markings Weight Limits 2-6 2-6 2-6 2-7 2-7 2-7 2-7 2-7 2-7 2-8 2-8 2-8 2-9 2-9 2-9 2-10 Center of Gravity Limits Normal Category . Utility Category Maneuver Limits. Normal Category . Utility Category Flight Load Factor Limits Normal Category. Utility Category Kinds of Operation Limits Fuel Limitations Placards 2-1/(2-2 blank) SECTION 1 GENERAL Arm Moment Center of Gravity (C. G.) C. G. Arm C.G. Limits Standard Empty Weight CESSNA MODEL 177B Arm is the horizontal distance from the reference datum to the center of gravity (C. G.) of an item. Moment is the product of the weight of an item multiplied by its arm. (Moment divided by the constant 1000 is used in this handbook to simplify balance calculations by reducing the number of digits.) Center of Gravity is the point at which an airplane, or equip- ment, would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. Center of Gravity Arm is the arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight. Standard Empty Weight is the weight of a standard airplane, including unusable fuel, full operating fluids and full engine oil. Basic Empty Basic Empty Weight is the standard empty weight plus the Weight weight of optional equipment. Useful Load Gross (Loaded) Weight Maximum Takeoff Weight Maximum Landing Weight Tare Useful Load is the difference between takeoff weight and the basic empty weight. Gross (Loaded) Weight is the loaded weight of the airplane. Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff run. Maximum Landing Weight is the maximum weight approved for the landing touchdown. Tare is the weight of chocks, blocks, stands, etc. used when weighing an airplane, and is included in the scale readings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. CESSNA MODEL 177B SECTION 2 LIMITATIONS TABLE OF CONTENTS Introduction Airspeed Limitations Center of Gravity Limits SECTION 2 LIMITATIONS Page 2-3 2-4 Airspeed Indicator Markings 2-4 Power Plant Limitations 2-5 Power Plant Instrument Markings Weight Limits 2-6 2-6 Normal Category. Utility Category 2-6 2-7 2-7 2-7 2-7 2-7 2-7 2-8 2-8 2-8 2-9 2-9 2-9 2-10 Normal Category. Utility Category Maneuver Limits. Normal Category. Utility Category Flight Load Factor Limits Normal Category . Utility Category Kinds of Operation Limits Fuel Limitations Placards 1-8 2-1/(2-2 blank) CESSNA MODEL 177B INTRODUCTION SECTION 2 LIMITATIONS 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 have been approved by the Federal Aviation Administration. When applicable, limitations associated with optional systems or equip- ment are included in Section 9. NOTE The airspeeds listed in the Airspeed Limitations chart (figure 2-1) and the Airspeed Indicator Markings chart (figure 2-2) are based on Airspeed Calibration data shown in Section 5 with the normal static source. If the alternate static source is being used, ample margins should be observed to allow for the airspeed calibration variations between the normal and alternate static sources as shown in Section 5. Your Cessna is certificated under FAA Type Certificate No. A13CE as Cessna Model No. 177B. 2-3 SECTION 2 LIMITATIONS AIRSPEED LIMITATIONS CESSNA MODEL 177B CESSNA MODEL 177B MARKING KIAS VALUE OR RANGE Airspeed limitations and their operational significance are shown in figure 2-1. White Arc 45 - 90 SPEED KCAS KIAS REMARKS VNE Never Exceed Speed 161 167 Do not exceed this speed in any operation. Green Arc 54 138 VNO Maximum Structural 134 138 Do not exceed this speed Cruising Speed except in smooth air, and Yellow Arc 138-167 then only with caution. VA Maneuvering Speed: 2500 Pounds 101 102 2100 Pounds 93 93 1700 Pounds 84 83 Do not make full or abrupt control movements above this speed. Red Line VFE Maximum Flap Extended Speed: To 10° Flaps 113 115 10° -30° Flaps 90 Maximum Window Open 104 ៩៖ 90 Do not exceed these speeds with the given flap settings. 105 Speed Do not exceed this speed with windows open. 167 SECTION 2 LIMITATIONS SIGNIFICANCE Full Flap Operating Range. Lower limit is maximum weight VSo in landing configuration. Upper limit is maximum speed permissible with flaps extended. Normal Operating Range. Lower limit is maximum weight Vs at most forward C.G. with flaps retracted. Upper limit is maximum structural cruising speed. Operations must be conducted with caution and only in smooth air. Maximum speed for all operations. Figure 2-2. Airspeed Indicator Markings Figure 2-1. Airspeed Limitations AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in figure 2-2. POWER PLANT LIMITATIONS Engine Manufacturer: Avco Lycoming. Engine Model Number: 0-360-A1F6D. Engine Operating Limits for Takeoff and Continuous Operations: Maximum Power: 180 BHP. Maximum Engine Speed: 2700 RPM. Maximum Cylinder Head Temperature: 260°C (500° F). Maximum Oil Temperature: 118°C (245°F). Oil Pressure, Minimum: 25 psi. Maximum: 100 psi. Fuel Pressure, Minimum: 2 psi. Maximum: 8 psi. Propeller Manufacturer: McCauley Accessory Division. Propeller Model Number: B2D34C211/82PCA-6. Propeller Diameter, Maximum: 76 inches. Minimum: 75 inches. Propeller Blade Angle at 30 Inch Station, Low: 12.1°. High: 26.0°. Propeller Operating Limits: Avoid continuous operation between 1700 and 1900 RPM with less than 10 inches manifold pressure. 2-4 2-5 CESSNA MODEL 177B MODEL 177 B SECTION 2 LIMITATIONS POWER PLANT INSTRUMENT MARKINGS CESSNA Power plant instrument markings and their color code significance are shown in figure 2-3. SECTION 2 LIMITATIONS NOTE The maximum combined weight capacity for cargo area 2 and the hatshelf is 120 lbs. The maximum weight capacity for the hatshelf is 25 lbs. RED LINE GREEN ARC YELLOW ARC RED LINE UTILITY CATEGORY INSTRUMENT MINIMUM LIMIT NORMAL OPERATING CAUTION RANGE MAXIMUM LIMIT Tachometer SL to 8000 Ft 2100 - 2500 RPM (inner arc) 1700 - 1900 RPM 2700 RPM 8000 Ft & above 2100 - 2700 RPM (outer arc) Manifold Pressure Oil Temperature Cylinder Head 15-24 in.Hg 100° - 245°F 245°F 200° - 500°F 500°F Temperature Fuel Pressure 2 psi 2 - 8 psi 8 psi Oil Pressure 25 psi 60-90 psi 100 psi Carburetor Air Temperature -15° to 5ºC Figure 2-3. Power Plant Instrument Markings WEIGHT LIMITS Maximum Takeoff Weight: 2200 lbs. Maximum Landing Weight: 2200 lbs. Maximum Weight in Baggage Compartment: In the utility category, the baggage compartment and rear seat must not be occupied. CENTER OF GRAVITY LIMITS NORMAL CATEGORY Center of Gravity Range: Forward: 101.0 inches aft of datum at 2000 lbs. or less, to 102.2 inches aft of datum at 2250 lbs., to 105.7 inches aft of datum at 2500 lbs., with straight line variation between points. Aft: 114.5 inches aft of datum at all weights. Reference Datum: 54.0 inches forward of front face of lower portion of firewall. UTILITY CATEGORY Center of Gravity Range: Forward: 101.0 inches aft of datum at 2000 lbs. or less, with straight line variation to 102.0 inches aft of datum at 2200 lbs. Aft: 109.0 inches aft of datum at all weights. Reference Datum: 54.0 inches forward of front face of lower portion of firewall. NORMAL CATEGORY Maximum Takeoff Weight: 2500 lbs. Maximum Landing Weight: 2500 lbs. Weight in Baggage Compartment, Normal Category: Baggage, passenger on auxiliary seat, or cargo area 2 and hatshelf - Station 142 to 185: 120 lbs. MANEUVER LIMITS NORMAL CATEGORY This airplane is certificated in both the normal and utility catego- ry. The normal category is applicable to aircraft intended for non- aerobatic operations. These include any maneuvers incidental to nor- 2-6 2-7 SECTION 2 LIMITATIONS CESSNA MODEL 177B mal flying, stalls (except whip stalls), lazy eights, chandelles, and turns in which the angle of bank is not more than 60°. Aerobatic ma- neuvers, including spins, are not approved. UTILITY CATEGORY This airplane is not designed for purely aerobatic flight. However, in the acquisition of various certificates such as commercial pilot, instru- ment pilot and flight instructor, certain maneuvers are required by the FAA. All of these maneuvers are permitted in this airplane when oper- ated in the utility category. In the utility category, the baggage compartment and rear seat must not be occupied. No aerobatic maneuvers are approved except those listed below: MANEUVER Chandelles. Lazy Eights Steep Turns Spins Stalls (Except Whip Stalls). RECOMMENDED ENTRY SPEED* 100 knots 100 knots 100 knots Slow Deceleration Slow Deceleration *Abrupt use of the controls is prohibited above 102 knots. Aerobatics that may impose high loads should not be attempted. The important thing to bear in mind in flight maneuvers is that the airplane is clean in aerodynamic design and will build up speed quickly with the nose down. Proper speed control is an essential requirement for execution of any maneuver, and care should always be exercised to avoid excessive speed which in turn can impose excessive loads. In the execution of all maneuvers, avoid abrupt use of controls. Intentional spins with flaps ex- tended are prohibited. FLIGHT LOAD FACTOR LIMITS NORMAL CATEGORY CESSNA MODEL 177B UTILITY CATEGORY Flight Load Factors (Gross Weight 2200 lbs.): *Flaps Up *Flaps Down . SECTION 2 LIMITATIONS +4.4g, -1.76g +3.5g *The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads. KINDS OF OPERATION LIMITS The airplane is equipped for day VFR and may be equipped for night VFR and/or IFR operations. FAR Part 91 establishes the minimum re- quired instrumentation and equipment for these operations. The refer- ence to types of flight operations on the operating limitations placard re- flects equipment installed at the time of Airworthiness Certificate issu- ance. Flight into known icing conditions is prohibited. FUEL LIMITATIONS 2 Standard Tanks: 25 U.S. gallons each. Total Fuel: 50 U.S. gallons. Usable Fuel (all flight conditions): 49 U.S. gallons. Unusable Fuel: 1.0 U.S. gallons. 2 Long Range Tanks: 30.5 gallons each. Total Fuel: 61 U.S. gallons. Usable Fuel (all flight conditions): 60 U.S. gallons. Unusable Fuel: 1.0 U.S. gallons. NOTE To ensure maximum fuel capacity when refueling, place the fuel selector valve in either LEFT or RIGHT posi- tion to prevent cross-feeding. NOTE Flight Load Factors (Gross Weight 2500 lbs.): *Flaps Up +3.8g, -1.52g +3.5g *Flaps Down *The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads. Takeoff and land with the fuel selector valve handle in the BOTH ON position. Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). 2-8 2-9 SECTION 2 LIMITATIONS PLACARDS CESSNA MODEL 177B The following information is 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 as the airplane is equipped.) CESSNA MODEL 177B (2) On control lock: Control lock - remove before starting engine. (3) On fuel shut-off control (at appropriate location): Fuel shut-off - pull off. This airplane must be operated in compliance with the operating limitations as stated in the form of placards, markings, and manuals. MANEUVERING SPEED (IAS) FLIGHT LOAD FACTOR GROSS WEIGHT MAXIMUMS Normal Category Utility Category 102 knots 102 knots 2500 lbs. Flaps Up Flaps Down • . +3.8, -1.52 +3.5 2200 lbs. +4.4, -1.76 +3.5 (4) On fuel selector valve (standard tanks): Both Left -- 49 gal. 24.5 gal. Right 24.5 gal. -- Both on for takeoff and landing. On fuel selector valve (long range tanks): Normal Category approved. Utility Category not be occupied. - - No acrobatic maneuvers including spins - Baggage compartment and rear seat must NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW Both -- 60 gal. Left 30 gal. -- Right 30 gal. -- Both on for takeoff and landing. SECTION 2 LIMITATIONS Maneuver Chandelles Lazy Eights Recm. Entry Speed . 100 knots Maneuver Recm. Entry Speed Spins Slow Deceleration . 100 knots Stalls (except Steep Turns . 100 knots Altitude loss in stall recovery whip stalls) Slow Deceleration -- 180 feet. - - neutralize Abrupt use of controls prohibited above 102 knots. Spin Recovery: opposite rudder forward stabilator controls. Intentional spins with flaps extended are prohibited. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: (5) Aft of fuel tank cap (standard tanks): Service this airplane with 91/96 minimum or 100/130 grade aviation gasoline. Total capacity 25.0 gal. Ca- pacity to line of holes inside filler neck 22.0 gal. Aft of fuel tank cap (long range tanks): 2-10 DAY - NIGHT - VFR-IFR Service this airplane with 91/96 minimum or 100/130 grade aviation gasoline. Total capacity 30.5 gal. Ca- pacity to line of holes inside filler neck 22.0 gal. 2-11 SECTION 2 LIMITATIONS CESSNA MODEL 177B (6) In baggage compartment: 120 pounds maximum baggage and/or auxiliary seat passenger, including 25 pounds maximum in baggage wall hatshelf. For additional loading instructions, see weight and balance data. (7) Next to door ventilation windows: Do not open window above 105 knots or when using alternate static source. CESSNA MODEL 177B. SECTION 3 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS (8) On wing flap indicator: 0° to 10° - 10° 20° 30° - (Blue color code and 115 knot callout; also, mechanical detent at 10°). (Indices at these positions with white color code and 90 knot callout; also, mechanical detent at 20°). Forced Landings. (9) On manifold pressure gage: With less than 10" manifold pressure, avoid con- tinuous operation between 1700-1900 RPM. (10) On the instrument panel near over-voltage light: 2-12 HIGH VOLTAGE Page Introduction 3-3 Airspeeds For Emergency Operation 3-3 OPERATIONAL CHECKLISTS Engine Failures 3-3 Engine Failure During Takeoff Run. Engine Failure Immediately After Takeoff Engine Failure During Flight 3-3 3-4 3-4 3-4 Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching. 3-4 3-4 3-5 Fires 3-5 . During Start On Ground 3-5 Engine Fire In Flight. 3-6 Electrical Fire In Flight 3-6 Cabin Fire 3-6 • Wing Fire. 3-7 Icing 3-7 Inadvertent Icing Encounter 3-7 Static Source Blockage (Erroneous Instrument Reading Suspected). 3-8 Landing With a Flat Main Tire. 3-8 Electrical Power Supply System Malfunctions 3-8 Over-Voltage Light Illuminates 3-8 Ammeter Shows Discharge 3-8 Engine Failures Forced Landings • AMPLIFIED PROCEDURES 3-9 3-10 3-1