Cessna 172 Aircraft Specifications PDF

# Cessna-172 Aircraft Specifications ## Aircraft Specifications - Elevator Span: 11'4" - Wing Span: 36'1" - Propeller Diameter: 75" max, 74" min - Max Height of ALC: 18'11" - Length of ALC: 27'2" - Wheel Base Length: 65" - Propeller Ground Clearance: 11.25" or 11' 1\4" - Wing Area: 174 sq ft - Min...

# Cessna-172 Aircraft Specifications ## Aircraft Specifications - Elevator Span: 11'4" - Wing Span: 36'1" - Propeller Diameter: 75" max, 74" min - Max Height of ALC: 18'11" - Length of ALC: 27'2" - Wheel Base Length: 65" - Propeller Ground Clearance: 11.25" or 11' 1\4" - Wing Area: 174 sq ft - Min Turning Radius: 27 ft 5.50 inches - Max Eng Speed for Takeoff & Continuous Operation: 2400 RPM ## Descriptive Data - Number of Engines: 1 - Engine Manufacturer: Textron Lycoming - Engine Model Number: 10-360-LZAO - Engine Type: Normally Aspitated - Direct Drive - Air Cooled - Horizontally Opposed - Fuel Injected - Four Cylinder Engine with 360 cu in. Displacement - Horsepower Rating & Engine Speed: 160 Rated BHP @ 2400 RPM # Propeller - Manufacturer: McCauley Propeller Systems - Model Number: 1C2350 / LFA 7570 - Number of Blades: 2 - Prop Diameter: 75 inches - Prop Type: Fixed Pitch # Fuel Capacity - Total Capacity: 56.0 US gallons - Total Usable: 53.0 US gallons - Total Capacity Each Tank: 28.0 US gallons - Total Usable Each Tank: 26.5 US gallons ## Approved Fuel Grades (and Colors) To Be Used - 100LL Grade Aviation Fuel (Blue) - 100 Grade Aviation Fuel (Green) # Utility Category Weight Note: - In Utility Category Weight, Rear Seat must not be occupied, and the baggage compartment must be empty ## Engine Oil Capacity - Sump: 8 US Quarts - Total: 9 US Quarts - Oil Type: MIL-L-6082 or SAE J1966 for first 50 hours. Straight Mineral Oil - MIL-L-22851 or SAE J1899 Ashless Dispersent Oil Note: When operating temperatures overlap, use the lighter grade of oil. ## Weight In Baggage Compartment, Normal Category - Baggage Area A (Station 82 to 108): 120 pounds - Baggage Area B (Station 108 to 142): 50 pounds - Max Bagage Combined Capacity: 120 pounds - Max Certified Weights: - Normal Category - Rampwt: 2457 pounds - TOwt: 2450 pounds - Landing Weight: 2450 pounds - Utility Category - 2207 pounds - 2100 pounds - 2400 pounds # Standard Airplane Weights - Standard Empty Weight: 1639 pounds - Max Useful Load, Normal Category: 818 pounds - Max Useful Load, Utility Category: 4068 pounds # Specific Loadings - Wing Loading: 14.1 lbs/sq ft - Power Loading: 15.2 lbs/HP - Tare: Is the weight of chocks, blocks, and stand etc. # Center of Gravity Range - Normal Category: Datum at 1950 pounds or less forward: 35.0 inches aft of datum at 1950 pounds; with straight lined variation to 40.0 inches aft of datum at 2450 pounds. - Aft: 47.3 inches aft of datum at all weights - 35'' at 1950 lbs - 40'' at 2450 lbs # Utility Category - Forward: 35.0 inches aft of datum at 1950 pounds or less, with straight lined variation to 36.5 inches aft of datum at 2200 pounds. - Aft: 40.5 inches aft of datum at all weights. ## Flight Load Factor - Normal Category: - Flight load factor (max TO weight: 2450 pounds): - Flaps up: +3.8g, -1.52g - Flaps down: +3.8g - Utility Category: - Flight Load Factor (max TO weight: 2200 pounds): - Flaps up: +4.4g, -1.76g - Flaps down: +3.8g ## Airspeeds - Airspeed Limitations: - VNE (KCAS): 160 - VNO (KCAS): 126 - VA (KCAS): - 2450 pounds: 197 - 2200 pounds: 98 - 1600 pounds: 82 - VFE (KCAS): 108 - Flaps 10° (KCAS): 84 - Flaps 10-30° (KCAS): 85 - Max Takeoff (KIAS): 160 - Open (KIAS): 163 ### Low Airspeed - Red arc (KIAS): 20-33 - White arc (kIAS): 33-85 - Green arc (KIAS): 44-129. Normal operating Range. - Yellow arc (KIAS): 129-163 - Redline (KIAS): 163. Max speed for all operations. ## Power Plant Limitations - Engine Operating Limits for TO & continuous operations: Max Engine Speed: 2400 RPM - Static RPM Range at Full Throttle: 2065-2165 RPM - Max Oil temp: 245°F (118°C) - Oil Pressure Min: 20 PSI - Oil Pressure Max 115 PSI ## Powerplant Instrument Markings - Tachometer: - Redline (1600): - Yellow ARC: 1900-2400 RPM - Green Arc: 2400-2700 RPM - CHT: 200° to 500°F - Oil Temp: 100°F to 245°F, 245°F to 625°F - Oil Pressure (inted 0 to 20 PSI): 50 to 90 PSI, 115 to 120 PSI - Fuel Quantily (Gallon Unusable Each Tank 0(1.5 Gallons: 0-5 Gallons, 5-24 Gallons - Full Flow: 0-119PH - Vacuum Indicator: 4.5 to 5.5 in. hg. ## Airspeeds For Emergency Operations - ENG Failure After TO: - Wing Flaps Up: 65 KIAS - Wing Flaps 10° FULL: 66 KIAS - Maneuvering Speed: - 2450 pounds: 99 KIAS - 2200 pounds: 94 KIAS - 1600 pounds: 82 KIAS - Max Glide: 65 KIAS - Precautionary Landing With Engine Power: 60 KIAS - Landing Without Engine Power: 65 KIAS - Wing Flaps Up: 65 KIAS - Wing Flaps 10° FULL: 60 KIAS ## Flaps Limitations - Approved TO Range: Up to 10° - Approved Landing Range: Up to Full # Important Points To Remember 1. Oil Pressure should register in cold weather in 60 seconds. 2. In the event of alternate static door open, air speed indicator will give on error of 4 knots and altimeter error will be 0 +/-30 in close window conditions. 3. Annunciator does not activate on low fuel flow and low RPM. 4. Alternator should be switched off in event of ammeter reading more than 31.5 volts. 5. Compass error upto 25 degrees in event of alternator switched off. 6. DGI should be aligned regularly on long haul flights for procession. 7. Audible stall warning will be heard above 5-10 knots above stall warning speed. 8. Attitude indicator has bank marking in an increment of 10, 20, 30, 60, 90. 9. Avionics cooling fan switches ON automatically when avionics master is ON. 10. Max oil quantity for extended flights is 8 quarts; Min is 5 quarts. 11. Concentration of DIEGME is 0.10% to 0.15% to be added to fuel. 12. MIL-L-22851 oil to be used after 50 hours of engine run up or when the consumption has stabilized. 13. Max deflection of nose wheel by use of rudder paddle on ground is 10 to either side. 14. Mechanical stops of flaps are at 10, 20, 30 degrees. 15. Shock absorption is accomplished by air/oil strut on nose wheel and tubular spring steel on main wheel. 16. Starter cycle for engine is 10 sec ON and 20 sec OFF for three times and then 10 minute gap for cooling is to be given. 17. Enroute climb speed is 5 to 10 knots above best ROC speed for best visibility, performance and cooling. 18. Until SO hours has been accumulated, engine should be run at 80% power on cruise. 19. An open alternate door will result in 10% loss of power at full throttle. 20. Carburator icing is indicated by loss of RPM in fixed pitch propeller and loss of manifold pressure in constant speed propeller. 21. Range - 580 nm Cruise power 80% - 122 knots. 22. Sound: 73 3dB at 2450 lbs 23. OAT / Voltmeter gauge select switch may be tested by putting the select button down for 3 seconds to start. 24. BET PTT button of microphone is kept pressed for more than 33 seconds in continuous, then the transmission is automatically terminated. 25. In the event of static tube blockage - AST reads error. 26. To permit heavy cabin loading, fuel load can be reduced to 17.5 gallons usable in each tank. 27. In Voltmeter / OAT? clock pushing upper control button will change the display on the window to E-CF- E - empty - full - center - empty. 28. All tyres are 6 ply rated - Nose wheel 6 ply rated - Main wheel. 29. The stall warning horn should be checked during pre flight by - master on, and actualing the vain in the wing, the system is operational if the stall tone is heard when the valve is pushed upward. 30. Engine driven vacuum pump provides suction to DGI and attitude indicator. 31. Pitot Static System provides pressure to ASI and static to PASI, VSI, Altimeter. 32. If the flashing beacon or lights are ON when flying through clouds at nights, it would reflect from water drops or particles and can cause: Verbigd and loss of orientation. 33. In Over Voltage Condn., the alternator control unit automatically removes the alternator field current and shuts down the alternator. 34. To apply parking break, apply the brakes with rudder pedals and pull the handle aft and turn 90 deg down. 35. Fuel system verifying is essential to the system operation. Blockages of the system will result in decreased fuel flow and even result in engine stopping. Verifying is accompanied by an interconnecting line from right to left fuel tank. 36. Tyre main pressure: 28 psi Main, 34 psi Nose. 37. Two Batteries of 24 Volts. MIL-H-5606 (One of ELT) 38. All DC supply: 28 Volts / 60 Amp - Alternator. 39. Volt. Capacity 24 Volt - Battery. 40. AHRS in tail of ALC. 41. Engine fire in air 100 kt speed should be maintained. 42. Oil Pressure: Min - 20 PSI, Green - 50-90 PSI, I15- PSI. 43. Fuel Flow: 0-11GPH. 44. Alternator should be switched off in an event of ammeters reading - more than 31.5 volts. 45. DG1 aligned on long flight for procession. Max deviation 30°. 3° in 15 min. 46. Min oil quantity for extended flights is 8 quarts. 47. Concen. in fuel of Isopropyl alcohol is 0.10%. 48. Shock absorption on nose wheel is - Air and oil system. 49. On Main wheel - Tubular Spring. 50. ALC clock model - Dautron model 803 digital clocks. 51. Landing with flat main tyre - Flaps 30°. 52. Engine failure during TO roll. First action is throttle idle. 53. Max speed at sea level: 123 kt. At 8000 ft, 80% PWR - 122 kt. 54. 80% power at 8000 ft Range: 580nm, 122 kts. 55. 52 US & fuel- 4.8 hours. 56. Range at 10,000 with 60% power: 687nm, time 6.6 hours 57. ROC at sea level: 720 FPM 58. Speed fairing inc. speed by 2kts. 59. Spin recovery - opp rudder, elevator down. 60. Calibration of magnetic compass in 30 increments. Accuracy of moqunhic compost - provide with flops. 61. Fire in flight maintain 100 KIAS. 62. Max. airspeed and altimeter varn: Normal is 30 ft, 4 kts with windows closed. (When primary source is blocked.) 63. Malfunction of alternator - Insoff, Rate of charge. 64. When the master switch is ON, annunciator will flash for 10 seconds. 65. During engine start master switch avionics should be switched off. 66. For cruise no more than 80% to power. 67. After 30 min. shutdown priming required. Cold Start. 68. In summer oil pressure should be regain in 30 sec. 69. Starter duty cycle. Crank 10 Sec. Cool Down 20 Sec. Repeat twice same followed by 10 min (cool down period). 70. Magneto Check: 1800 RPM - Max 150, diff 50. 71. Alternator check - can be done by loading electrical load & flaps (3-5 sec). 72. Using flaps 10° reduces ground roll and total dis. over an obstacle by 10%. 73. Best economy - peak EGT. 0-4.5% - 3 - 4% greater range. 3 KT decrease in speed. 74. Baggage tiedown is nylon 6 bolt. 75. Airframe Structure - Semi Monoque. Aluminium Skin. V-Shaped. 76. Nose Wheel - 10° by Rudder, 30° by rudder / brakes. 77. Accidental opening of cabin door - Mnth 75 kts. 78. Residual oil is returned to sump by gravity flow. 79. An open alternate door result in 10% power loss at full throttle. 80. Low voltage annunciator. Volt. falls below 24.5 volts. 81. Annunciator doesn't activate on low fuel flow & low RPM. 82. Altitude indicator 10°, 20°, 30°, 60°, 90°. 83. Static discharges should be check every year. 84. Autopilot circuit breaker - 28 VDC, 5 amp, CB, 6 amp. 85. KAP 140 system: - Ground Roll: 945 ft - Landing Roll: 550 ft. - 4.8 hrs @ sea level - 6.6 hrs @ 10,000 ft 86. Fire extinguisher on board - Halon 1211. 87. Vacuum instrument - daily, at 125 PS. 88. Max payload onboard - 17.5 us gallons fuel can be carried. 89. Mixture should be lean after on elevation of 3000 ft. 90. Autopilot Engage: - Max. Airspeed limitation: 140 kts. - Min. Airspeed limitation: 70 kts. - Min app. speed: 80 kts. 91. Lights on annunciator panel: - Red - Fuel transmitter: Less than 5 gallons for more than 60 sec. - Amber - Low oil pressure: Less than 20 PSI. - Amber - Vacuum transducer: Less than 3.0 in of Hg. - Amber - ACU volts: 24.5. 92. Mode C transponder in ALC: Stat, Elevation, Sqwk. 93. Parking brakes: Single disc plate hydraulic. 94. Flaps: Simple single slot flaps. 95. MEGT: 1125° - 1550°F. 96. Max height can be flown without oxygen: 10,000 ft (Anc: 9,800 ft) 97. Nose wheel shut length: 2 inch. 98. Lapse Rate: 2°C/ 1000 ft. 99. Main wheel brakes type: Hydraulically actuated single disc brake.