14 CFR § 121.305

An airspeed indicating system with heated pitot tube or equivalent means for preventing malfunctioning due to icing.

A sensitive altimeter.

A sweep-second hand clock (or approved equivalent).

A free-air temperature indicator.

A gyroscopic bank and pitch indicator (artificial horizon).

A gyroscopic rate-of-turn indicator combined with an integral slip-skid indicator (turn-and-bank indicator) except that only a slip-skid indicator is required when a third attitude instrument system usable through flight attitudes of 360° of pitch and roll is installed in accordance with paragraph (k) of this section.

A gyroscopic direction indicator (directional gyro or equivalent).

A magnetic compass.

A vertical speed indicator (rate-of-climb indicator).

On the airplane described in this paragraph, in addition to two gyroscopic bank and pitch indicators (artificial horizons) for use at the pilot stations, a third such instrument is installed in accordance with paragraph (k) of this section:

On each turbojet powered airplane.

On each turbopropeller powered airplane having a passenger-seat configuration of more than 30 seats, excluding each crewmember seat, or a payload capacity of more than 7,500 pounds.

On each turbopropeller powered airplane having a passenger-seat configuration of 30 seats or fewer, excluding each crewmember seat, and a payload capacity of 7,500 pounds or less that is manufactured on or after March 20, 1997.

After December 20, 2010, on each turbopropeller powered airplane having a passenger seat configuration of 10-30 seats and a payload capacity of 7,500 pounds or less that was manufactured before March 20, 1997.

When required by paragraph (j) of this section, a third gyroscopic bank-and-pitch indicator (artificial horizon) that:

Is powered from a source independent of the electrical generating system;

Continues reliable operation for a minimum of 30 minutes after total failure of the electrical generating system;

Operates independently of any other attitude indicating system;

Is operative without selection after total failure of the electrical generating system;

Is located on the instrument panel in a position acceptable to the Administrator that will make it plainly visible to and usable by each pilot at his or her station; and

Is appropriately lighted during all phases of operation.