Data Sheet: Cessna 172S

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PURDUE AVIATION Weights Data Sheet: Cessna 172S May 21, 2019 A/C # Empty Weight Empty Moment Arm Useful Load N651PA 1708.4 lbs. 72,338 42.3 841.6 lbs. N652PA 1708.5 lbs. 72,338 42.341 841.5 lbs. N653PA 1708.4 lbs. 72,330 42.3 841.6 lbs. N654PA 1682.6 lbs. 69,496 41.3 867.4 lbs. N665CS 1715.4 lbs. 72,082.9 42.021 842.6 lbs. N618JM 1664.3 67,584.35 40.61 885.70 Compass Deviations N651PA N 30 60 E 120 150 360 30 60 91 122 152 S 210 240 W 300 330 182 210 240 270 300 330 N652PA N 30 60 E 120 150 360 30 62 92 122 153 S 210 240 W 300 330 182 211 241 270 300 330 N653PA N 30 60 E 120 150 360 30 62 92 122 153 S 210 240 W 300 330 182 211 241 270 300 330 1 PURDUE AVIATION May 21, 2019 N654PA N 30 60 E 120 150 360 30 58 89 120 150 S 210 240 W 300 330 179 209 239 270 301 330 N665CS N 30 60 E 120 150 360 30 60 89 120 150 S 210 240 W 300 330 180 210 240 270 300 331 N618JM N 30 60 E 120 150 358 27 57 87 117 148 S 210 240 W 300 330 179 209 239 268 299 328 Maximum Weights Normal Utility Ramp Weight 2558 lbs. 2208 lbs. Takeoff Weight 2550 lbs. 2200 lbs. Landing Weight 2550 lbs. 2200 lbs. Baggage Weight 120 lbs. empty Area 1 120 lbs. empty Area 2 50 lbs. empty 2 PURDUE AVIATION May 21, 2019 Power-plant Number of Engines: 1 Engine Manufacturer: Textron Lycoming Engine Model Number: 10-360-L2A Number of cylinders: 4 Engine Type: Normally aspirated, direct drive, air-cooled, horizontally opposed, fuel injected, four cylinder engine with 360.0 cu. in. displacement. Horsepower Rating and Engine Speed: 180 rated BHP at 2700 RPM Maximum Engine Speed:. Maximum Oil Temperature: Oil Pressure, Minimum: Oil Pressure, Maximum: .2700 RPM .245°F (118°C) ..20 PSI .115 PSI Brake System SYSTEMS DESCRIPTION: The airplane has a single-disc, hydraulically-actuated brake on each main landing gear wheel. Each brake is connected, by a hydraulic line, to a master cylinder attached to each of the pilot's rudder pedals. The brakes are operated by applying pressure to the top of either the left (pilot's) or right (copilot's) set of rudder pedals, which are interconnected. When the airplane is parked, both main wheel brakes may be set by utilizing the parking brake which is operated by a handle under the left side of the instrument panel. To apply the parking brake, set the brakes with the rudder pedals, pull the handle aft, and rotate it 90° down. For maximum brake life, keep the brake system properly maintained, and minimize brake usage during taxi operations and landings. Fuel System Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue) 100 Grade Aviation Fuel (Green) FUEL CAPACITY Total Capacity. Total Usable . . Total Capacity Each Tank. .56.0 U.S. GALLONS .53.0 U.S. GALLONS .28.0 U.S. GALLONS .26.5 U.S. GALLONS Total Usable Each Tank . ***To ensure maximum fuel capacity and minimize cross feeding when refueling, always park the airplane in a wings level, normal ground attitude and place the fuel selector in the LEFT or RIGHT position. 3 PURDUE AVIATION May 21, 2019 SYSTEMS DESCRIPTION: The engine is equipped with a fuel injection system. The system is comprised of an engine driven fuel pump, fuel/air control unit, fuel manifold, fuel flow indicator, and air-bleed type injector nozzles. Fuel is delivered by the engine driven fuel pump to the fuel/air control unit. The fuel/air control unit correctly proportions the fuel flow to the induction air flow. After passing through the control unit, induction air is delivered to the cylinders through the intake manifold tubes and metered fuel is delivered to a fuel manifold (flow divider). The fuel manifold, through spring tension on a diaphragm and valve, evenly distributes the fuel to an air- bleed type injector nozzle in the intake valve chamber of each cylinder. A turbine-type fuel flow transducer mounted between the fuel/air control unit and the fuel distribution unit produces a digital signal that displays fuel flow on the EIS pages. Electrical System Alternator- 28 volt, 60 ampere Battery- 24 volt SYSTEMS DESCRIPTION: Power is supplied to most electrical circuits through two primary buses (ELECTRICAL BUS 1 and ELECTRICAL BUS 2), with an essential bus and a crossfeed bus connected between the two primary buses to support essential equipment. The system is equipped with a secondary or standby battery located between the firewall and the instrument panel. The STBY BATT switch controls power to or from the standby battery. The standby battery is available to supply power to the essential bus in the event that alternator and main battery power sources have both failed. The primary buses are supplied with power whenever the MASTER switch is turned on, and are not affected by starter or external power usage. Each primary bus is also connected to an avionics bus through a circuit breaker and the AVIONICS BUS 1 and BUS 2 switches. Each avionics bus is powered when the MASTER switch and the corresponding AVIONICS switch are in the ON position. Pitot-Static System and Instruments SYSTEMS DESCRIPTION: 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 pitot-static instruments to the sources. The heated pitot system uses an electrical heating element built in the body of the pitot head. The PITOT HEAT control switch is found on the switch panel below the lower left corner of the PFD. The PITOT HEAT circuit breaker is found on the circuit breaker panel at the lower left side of the pilot panel. 4 P PURDUE AVIATION May 21, 2019 A static pressure alternate source valve (ALT STATIC AIR) is located adjacent to the throttle control. The ALT STATIC AIR valve provides static pressure from inside the cabin if the external static pressure source becomes blocked. If erroneous instrument readings are suspected due to water or ice in the pressure line going to