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The pitot air system consists of a pitot mast located on the underside of the left wing, with its related plumbing. Impact air pressure entering the pitot is transmitted from the pitot inlet through hose and tubing routed through the wing to the airspeed indicator on the instrument panel. A partially or completely blocked pitot head will give erratic or zero reading on the instruments.
Static air system consists of a static port located on the bottom of the pitot mast. The static port is directly connected to the airspeed indicator, altimeter and rate of climb indicator on the instrument panel by means of hose and tubing routed through the wing along with the pitot line. An alternate static air source is located below the instrument panel in front of the pilot. The alternate static source is part of the standard system and has a shutoff valve which closes the port when it is not needed. A placard giving instructions for use is located on the instrument panel. Pitot and static lines can be drained through separate drain valves located on the left lower side of the fuselage interior.
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Figure 34-1. Pitot-Static System Installation 
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FLIGHT ENVIRONMENT DATA AND PITOT STATIC.
VERTICAL SPEED INDICATOR.
The Vertical Speed Indicator (VSI) measures the rate of change in static pressure when the airplane is climbing or descending. By means of a pointer and dial, this instrument will indicate the rate of ascent or descent of the airplane in feet per minute. Due to the lag of the instrument, the aircraft will be climbing or descending before the instrument gives the correct rate. The instrument will continue to read after the aircraft has assumed level flight. In rough air this should not be considered a malfunction.
ALTIMETER.
The altimeter indicates altitude in feet above mean sea level. The indicator has three pointers and a dial scale, the long pointer is read in hundreds of feet, the middle pointer in thousands of feet and the short pointer in tens of thousands of feet. A barometric pressure window is located on the right side of the indicator dial and is set by the knob located on the lower left corner of the instrument. The altimeter consists of a sealed diaphragm that is connected to the pointers through a mechanical linkage. The instrument case is vented to the static air system and as static air pressure decreases, the diaphragm expands, causing the pointers to move through the mechanical linkage to indicate a higher altitude.
AIRSPEED INDICATOR.
The airspeed indicator indicates the speed of the airplane passing through the air. The airspeed indication depends on the differential pressure between pitot (ram) air pressure and static air pressure. This instrument has the diaphragm vented to the pitot air source and the case is vented to the static air system. As the airplane increases speed, the pitot air pressure increases, causing the diaphragm to expand. A mechanical linkage picks up this motion and moves the instrument pointer to the indicated speed. The instrument dial is calibrated in knots and miles per hour, and also has markings indicating the safe airspeed operating range of the airplane.
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CHART 3401. TROUBLESHOOTING (VERTICAL SPEED INDICATOR)

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CHART 3402. TROUBLESHOOTING (ALTIMETER)

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CHART 3403. TROUBLESHOOTING (AIRSPEED TUBES AND INDICATOR)

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ATTITUDE AND DIRECTION.
ARTIFICIAL HORIZON.
Air driven or electric artificial horizons are used depending on the option package installed. Both types are displacement type gyros with “free” rotors mounted in gimbal assemblies. Important: Consult the A.F.C.S. Manufacturer's Service Manual, if a flight director or autopilot is coupled to the artificial horizon.
AIR DRIVEN ARTIFICIAL HORIZON.
The air driven artificial horizon is driven by the pneumatic system which is supplied by engine driven dry pneumatic pumps either on pressure or vacuum. Note that air VOLUME and not air pressure, spins the gyro rotor. The air filter can become contaminated and restrict air flow reducing gyro rotor speed while the pressure regulator will automatically adjust air pressure within proper limits.
— Note —
The gyro air filter must be clean or replaced prior to adjusting gyro air pressure.
Airflow directed at the gyro buckets causes the rotor spin approximately 17,000 to 22,000 rpm thus producing the gyroscopic ability to remain rigid in space. The instrument case moves freely about the spinning gyro rotor in three dimensions by use of a gimbal assembly. The resulting displacement in both pitch and roll is mechanically displayed on the instrument face, providing an artificial horizon reference which portrays airframe attitude at any given moment. The display is stable and can show minute attitude changes of only 1°. Unlike the directional gyro, the erection mechanism activity can be seen by a rapidly wobbling and leveling horizon bar when power is first applied. The instrument can be adjusted for parallax through a knob on the instrument face. This knob, when held in the “IN” position, engages forks which cage the gyro rotor.
　
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