Pitot Static system Piper Archer III PA-28-181 step by step,

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PITOT-STATIC SYSTEM

The system supplies both pitot and static pressure for the airspeed indicator, altimeter and the vertical speed indicator.

Pitot and static pressure are picked up by a pitot head installed on the bottom of the left wing and carried through pitot and static lines within the wing and fuselage to the gauges on the instrument panel.

An alternate static source is standard equipment. The control valve is located below the left side of the instrument panel. When the valve is set in the alternate position, the altimeter, vertical speed indicator and airspeed indicator will be using cabin air for static pressure. The storm window and cabin vents must be closed and the cabin heater and defroster must be on during alternate static source operation. The altimeter error is less than 50 feet unless otherwise placarded.

Both the pitot and static lines can be drained through separate drain valves located on the left lower side of the fuselage interior. A heated pitot head, which alleviates problems with icing and heavy rain, is standard equipment. The switch for the heated pitot head is located on the electrical switch panel above the throttle quadrant. To prevent bugs and water from entering the pitot and static pressure holes, a cover should be placed over the pitot head. A partially or completely blocked pitot head will give erratic or zero readings on the instruments.

👉 PIPER ARCHER III PA 28-181 HANDBOOK

👉 PREFLIGHT INSPECTION

👉 MISCELLANEOUS

👉 BEFORE STARTING ENGINE

👉 NORMAL START - COLD ENGINE

👉 NORMAL START - HOT ENGINE

👉 ENGINE START WHEN FLOODED

👉 STARTING WITH EXTERNAL POWER

👉 WARM-UP

👉 TAXIING

👉 GROUND CHECK

👉 BEFORE TAKEOFF