Section XI. FLIGHT INSTRUMENTS
The pitot system (fig. 2-38) provides ram air
pressure for the airspeed indicators and air data
computer. The pitot system consists of two pitot masts
(one located on each side of the lower portion of the
nose), and associated plumbing. The pitot masts are
protected from ice formation by internal electric heating
STATIC AIR SYSTEM.
Description. The static system (fig. 2-38)
provides static air pressure for the pilot's and copilot's
computer, and pilot's and copilot's vertical speed
indicators. The static air pressure ports are located on
the right and left sides of the aft fuselage exterior skin.
Alternate Static Air Source. An alternate static
air line, which terminates just aft of the rear pressure
bulkhead, provides a source of static air for the pilot's
instruments in the event of source failure from the pilot's
static air line. A control on the pilot's subpanel
ALTERNATE air source by a two position selector valve.
The valve is secured in the NORMAL position by a
A turn-and-slip indicator is installed on the pilot's
side of the instrument panel (fig. 2-18). This indicator is
gyroscopically operated and electrically powered through
a 5-ampere circuit breaker placarded TURN & SLIP,
located on the overhead circuit breaker panel (fig. 2-9).
Two identical airspeed indicators are installed
separately on the pilot's and copilot's sides of the
instrument panel (fig. 2-18). These indicators require no
electrical power for operation. The indicator dials are
calibrated in knots from 40 to 300. A striped pointer
automatically displays the maximum allowable airspeed
at a given aircraft altitude.
Figure 2-38. Pitot and Static System