Any of the six air vents can control the amount of fresh air entering the cabin. One near each upper corner of the windshield supplies air for the pilot and passenger. The forward cabin heat and ventilation air flows through exit holes arranged across the cabin divider just in front of the pilot's and co-passenger's feet.
Rear cabin heat and air flow through two ducts from the manifold, one extending down each side of the cabin to an outlet just behind the floor-level control pedals. Windshield defrost air is supplied by two ducts leading from the cabin manifold to the defrost outlets near the lower edge of the windshield. The temperature and volume of air flow into the cabin can be regulated by adjusting the CABIN HT and CABIN AIR control knobs.
With the CABIN AIR control fully back and the CABIN HT control fully forward, only ambient air flows through the heated air distribution system. Fresh air outlet valves are located in the cockpit/cabin, in the upper corners of the windshield, in the side walls just behind the instrument panel and above the passenger seat.
AVIONICS COOLING FAN - MAINTENANCE PRACTICES (21-21-00)
COOLING FANS
TAILCONE STAND
Heating and Defrosting
HEATING AND DEFROSTING - DESCRIPTION AND OPERATION (21-40-00)
The cabin heater system works by passing ambient air through an exhaust shield where it is heated before flowing into the cabin. A crack in the exhaust pipe in the area surrounded by the casing could cause an exhaust leak, which would allow exhaust gases to mix with the heated ambient air flowing into the cabin. So, if someone in the cabin smells exhaust fumes, experiences any symptoms, or the CO LVL HIGH warning goes on when using the cabin heater, turn the cabin heater off immediately.
As the air passes through the heat exchanger and around the exhaust seal, it picks up heat from the engine exhaust. This hot air exits the heat exchanger and flows through the duct to a firewall shutoff valve.
FRESH AIR
HEATING AND DEFROSTING MAINTENANCE PRACTICES (21-40-00)
HEAT EXCHANGER
Most heated air distribution system components are riveted to the airframe and do not require replacement during normal maintenance.
HEATING AND DEFROSTING MAINTENANCE PRACTICES (21-40-00)
Environmental System Review
Model Differences
182/206 DIFFERENCES - FRESH AIR DISTRIBUTION (21-20-00)
There is one in each wing leading edge, for air intake vents located in the cockpit/cabin area at the wing roots at the top corners of the windshield, in the sidewalls just behind the instrument panel and above the passenger seat. A door assembly, located on the right side of the hull between the fire wall and the door post, also allows fresh air to be directed into the heating ducts. Four of these sources are located on the leading edge of the wing (two left and two right).
The other two sources are located on the left and right sides of the hull, just aft of the firewall. Fresh air from the outer front air intakes is distributed via ducting to adjustable air outlet flaps (Wemacs) in the top corner of the windshield and between the instrument panel and the front door frame. The inboard scoops on each wing distribute fresh air through ducts to adjustable air outlet flaps (Wemacs), two on each side, at the top of the aft cabin.
Fresh air entering from the left and right sides of the hull is controlled by scoops (doors) which can be placed in any position. Door assemblies located on the left and right sides of the hull just after the firewall also allow fresh air to be directed into the heat ducts.
182/206 DIFFERENCES - FRESH AIR DISTRIBUTION (21-20-00)
182/206 DIFFERENCES - REMOTE AVIONICS COOLING FAN - (21-21-00)
182/206 DIFFERENCES - HEATING AND DEFROSTING - (21-40-00)
Heat and air in the aft cabin are supplied through two ducts from the manifold, one of which extends on either side of the cabin to an outlet just behind the floor-level rudder pedals. Windshield defrosting air is also supplied through two ducts from the manifold outlet in the cab on top of the glareshield; therefore the defrost air temperature is the same as the heated cabin air. Also located to the right of the cab air knob is an Aux Cab Air Control knob.
The temperature and volume of cabin air flow can be adjusted by manipulating the CABIN HEATING, CABIN AIR and AUX CABIN AIR controls. When partial cabin heat is desired, the mixing of warm and cold air will result in improved ventilation and heat distribution throughout the cabin. Additional outside air for summer ventilation is provided through the heating and ventilation system using the AUX CABIN AIR control switch.
Forward cabin heat and ventilation air are supplied from vents located along a cockpit manifold just forward of the pilot's and front passenger's feet. Heating and air to the rear cabin are supplied by three ducts from the manifold, one outlet in each area of the front pillar at floor level and one extending under the center of the cabin floor to an outlet in the floor behind the pilot and passenger seats. Windshield defrost air is also supplied by a duct from the cabin manifold to an outlet on top of the heated windshield; therefore, the temperature of the defrost air is the same as that of the heated cabin air.
The cabin heater system works by passing ambient air through an exhaust shield where it is heated before being introduced into the cabin. If an exhaust leak, caused by a crack in the exhaust pipe, occurs in the area enclosed by this casing, it will allow exhaust gases to mix with the heated ambient air that is directed into the cabin. If anyone in the cabin smells exhaust fumes, experiences any of the symptoms mentioned above, or the CO LVL HIGH warning comes on when the cabin heater is in use, turn the cabin heater off immediately.
The 206 valve body of the heat plenum attaches to the firewall on the LEFT side of the aircraft. The distribution plenum in the cockpit area is bolted to the firewall and the other components of the heated air distribution system are connected to the distribution plenum in the cockpit area by means of ducts connected by clamps. The shutoff valve is attached to the firewall and is not removed from the aircraft during normal maintenance.
182 COCKPIT-AREA DISTRIBUTION PLENUM
Part of this air is directed towards a starting point in the rear engine shield. This air is led via duct to the heat exchanger part around the left exhaust muffler. As air passes into the heat shield and around the exhaust muffler, it absorbs heat from the engine's exhaust.
The shut-off valve is cable controlled from the cockpit and controls the amount of heated air entering the cockpit distribution space. Ground air enters the engine compartment through the forward baffle opening located at the rear of the propeller. This air passes through a pipe to the heater housing to exchange heat around the exhaust manifold at the front end of the engine.
As air passes into the heater jacket and around the exhaust manifold, it receives heat from the engine exhaust. The shut-off valve is cable controlled from the cockpit and controls the flow of heated air entering the cockpit area distribution plenum.
206 COCKPIT-AREA DISTRIBUTION PLENUM
182/206 DIFFERENCES - HEATING AND VENTILATION CONTROL CABLE SERVICING (12-21-05)
L-700 GENERAL PURPOSE LUBE OIL
ATA30 - Ice and Rain Protection Overview
LESSON OBJECTIVES
Propeller Heat
DESCRIPTION AND OPERATION (30-60-00)
182/206 PROPELLER HEAT - DESCRIPTION AND OPERATION (30-60-00)
182/206 PROPELLER HEAT - MAINTENANCE PRACTICES (30-60-00) PROPELLER HEAT TIMER/MONITOR
182/206 PROPELLER HEAT - MAINTENANCE PRACTICES (30-60-00) DEICE BOOTS REMOVAL/INSTALLATION
PROPELLER HEAT SYSTEM
182/206 PROPELLER HEAT - MAINTENANCE PRACTICES (30-60-00)
ELECTRICAL POWER
ATA35 Oxygen System Overview
OXYGEN SYSTEM - DESCRIPTION AND OPERATION (35-01-00)
The pilot mask supply line gives a greater flow of oxygen than the passenger mask supply lines. A four-place oxygen system provides the supplemental oxygen needed for sustained high-altitude flight. Four oxygen outlets are provided; two in the overhead oxygen panel and two in the cabin ceiling just above the side windows (one in each of the rear seating positions).
A six-place oxygen system provides the supplemental oxygen necessary for continuous flight at high altitude. Six oxygen outlets are provided; two in the overhead oxygen console and four in the cabin ceiling just above the side windows (one at each of the rear seats).
OXYGEN CONTROL VALVE KNOB
Oxygen flow to the exhaust ports begins when the oxygen control valve knob, located in the overhead console, is moved to the ON position and mask tubing is connected to the air oxygen ports.
OXYGEN PORT
The oxygen cylinder has the following information on the shoulder, neck or top of the cylinder to aid in correct identification. The symbol of the purchaser, user or manufacturer, if registered with the Bureau of Explosives, can be found directly below the serial number. The cylinder serial number can be found in an alternate location on the upper cylinder head.
The dash between the month and the year figures can be replaced with the mark of the inspection agency or agency that performs the test. The dates of subsequent hydrostatic tests must be stamped directly below the original manufacturer's date with a steel stamp (month and year). The dash between the month and year figures can be replaced with the mark of the testing agency.
The phrase "Halogen Tested", the test date (month, day and year) and the inspector's mark are located below the Cessna identification card. The cylinder pressure is reduced to a working pressure of 70 PSI by a pressure regulator attached to the cylinder. An oxygen cylinder fill valve is located on the left side of the fuselage tail under a cover plate.
Cylinder pressure is indicated by a pressure gauge located in the overhead oxygen console above the pilot and front passenger seats.
OXYGEN- MAINTENANCE PRACTICES (35-01-00)
FLAMMABLE
AIR COMPRESSOR
PRECAUTIONS
SPARKS
OXYGEN BOTTLE
OXYGEN SYSTEM
REPLACEMENT OF COMPONENTS
CAP LINES
OXYGEN CYLINDER AND REGULATOR ASSEMBLIES
HIGH PRESSURE FITTINGS
OXYGEN RELEASE INDICATOR DISC
INDICATOR DISC
CONNECTIONS
OXYGEN SYSTEM CHARGING
GROUND
CONTAMINATION
ATA37 Vacuum System Overview
VACUUM SYSTEM DESCRIPTION AND OPERATION (37-00-00)
The standby indicator is a vacuum powered gyroscopic instrument located on the center instrument panel below the MFD. The attitude indicator includes a low vacuum warning flag (GYRO) that comes into view when the vacuum drops below the level necessary for reliable gyroscope operation. The vacuum indicator is located on the EIS ENGINE page, located on the left side of the PFD during engine starting or on the left side of the MFD during normal operation.
During return operation, the EIS bar appears along the left side of the operational display.
Vacuum System Troubleshooting (37-10-00)
VACUUM SYSTEM TROUBLESHOOTING (37-10-00)
Vacuum System Maintenance Practices (37-10-00)
VACUUM PUMP
VACUUM SYSTEM MAINTENANCE PRACTICES (37-10-00)
GASKETS
VISE
TEFLON TAPE
GARMIN G1000
INSPECT/TEST FOR LEAKS
Vacuum System Review
VACUUM SYSTEM SUMMARY (37-00-00)
182/206 DIFFERENCES - VACUUM SYSTEMS (37-10-00)
