(a)   both function takes place in a single unit or instrument.

Requires information to be sensed or captured and then sent to separate display unit in the cockpit.

(a)  

Designed to measure operation parameters of the aircraft engine. They are usually quantity, pressure and temperature. Also includes measuring engine speed.

(a)  

Instrument that indicates the speed of the crankshaft of a reciprocating engine. Connected to the engine by a flexible drive shaft and geared to the engine so that when the engine turns, so does the shaft.

(a)  

Indicates the pressure of the air in the engine's induction manifold. Indication of the power to develop in the engine. (the higher the pressure of fuel air mixture in the engine, the more power it can produce). It is calibrated in inches of mercury.

(a)  

Indicates the approximate gallons per hour being metered to the engine. Connected on the fuel manifold valve.

(a)  

A bourdon tube type or electrically operated indicator. The gauge is connected by a single wire to sending unit located in the engine oil passage above the oil cooler.

(a)  

Bourdon tube type direct reading gauge operated by a pressure pickup line connected to the engine main oil gallery. The most important instrument used by the pilot to perceive the health of an engine. The normal operating range is represented by green arc. It is indicated in PSI.

(a)  

(a)   is connected to a thermocouple on the engine cylinder. All cylinder have a provision of the installation of thermocouple.

The instruments used in controlling aircraft's flight attitude.

(a)  

Differential pressure gauge that compares ram air pressire and static pressure. It is calibrated in miles per hour and knots.

(a)  

Used to indicate the height of the aircraft above a predetermined level, such as sea level or terrain beneath the aircraft. Operated by the static air from the static air from the static pressure port located on both side of the aft fuselage thru tubing. Direct reading instrument calibrated in feet.

(a)  

Indicates the actual climb or descent rate of the aircraft. Operated by atmospheric pressure thru static system of the aircraft. Calibrated in feet per minute.

(a)  

Indicates the attitude of the aircraft during flight. Give the pilot pitch and roll information, operated by vacuum system and suction gauge reading of 5.3 inches of mercury is desirable for gyro instruments like (a)   .

Shows the correct execution of a turn while banking the aircraft and indicates movement about the vertical axis of the aircraft. Powered by aircraft electrical system and operates only when the power is on.

(a)  

Contribute information used by pilot to guide the aircraft along definite course.

(a)  

Shows the aircraft heading relative to magnetic North. Operates through the earth's magnetic field.

(a)  

Furnishes the pilot a constant directional reference with relation to the north pole of the earth. Synchronized with standby compass and operated by the vacuum system.

(a)  

Measures and indicates the alternator output voltage of the electrical system.

(a)  

Part of vacuum system that indicate inches of mercury (in Hg); green markings indicate to inches of mercury which is the operating range for the gyro instrument Hg is desirable at full power.

(a)  

Indicates the position of the the flaps extended downward through a flaps position transmitter. it is electrically operated through a low voltage regulator.

(a)  

Used in conjunction with a float operated variable-resistance transmitter in its fuel tank.

(a)  

VACUUM PUMP:

(a)   is provided by the engine driven pump mounted

in the engine accessory case.

(a)   is used to control system pressure.

(a)   is utilized located inside the cockpit.

(a)   indicates the net difference in pressure before and after passing through a gyro.