TM 1-1510-218-10
2-116
Section XI. FLIGHT INSTRUMENTS
2-88. PITOT AND STATIC SYSTEM.
NOTE
Instrument panels for each model aircraft
are shown in Figure 2-17.
a. Description. The pitot and static system
provides a source of impact air and static air for the
operation of flight instruments. A heated pilot mast is
located on each side on the lower portion of the nose.
Tubing from each mast extends into the cabin to the
instrument panel for the instruments. Refer to Figure
2-31.
b. Normal Static System. The normal static
system provides two sources of static air to the flight
instruments through two static air fittings on each side
of the aft fuselage. Each static system utilizes one
static button on each side of the fuselage.
c. Alternate Static System. An alternate static
airline that 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,
placarded PILOT'S STATIC AIR SOURCE, may be
actuated to select either NORMAL or ALTERNATE air
source by a two-position selector valve. A valve is
secured in the NORMAL position by a spring clip.
Altimeter and airspeed information graphs are
provided in the Performance section for computation
when operating on normal or alternate static air.
d. Static Line Drains. There are three drain
petcocks for draining the static air lines located on the
right lower sidewall. These are protected by an
access cover, placarded STATIC AIR LINE DRAIN.
These drain petcocks should be opened to release any
trapped moisture at each 100-hour inspection, or more
often if conditions warrant, and must be closed after
draining.
2-89. TURN-AND-SLIP INDICATORS C D1 .
Turn and slip indicators are installed separately
on the pilot and copilot sides of the instrument panel,
Figure 2-17, Sheet 1. The pilot's indicator provides
yaw damping information to the autopilot. These
indicators are gyroscopically operated. They use dc
power and are protected by 5-ampere circuit breakers,
placarded TURN & SLIP PILOT or COPILOT, on the
overhead circuit breaker panel.
2-90. TURN-AND-SLIP INDICATORS D2 .
Turn and slip indicators are installed separately
on the pilot and copilot sides of the instrument panel,
Figure 2-17, Sheet 2. These indicators are
gyroscopically operated. The pilot's turn and slip
indicator uses dc power, protected by a 5-ampere
circuit breaker, placarded TURN & SLIP PILOT,
located on the overhead circuit breaker panel. The
copilot's turn and slip indicator does not require
electrical power.
2-91. TURN-AND-SLIP INDICATOR T .
Only one turn and slip indicator is installed on
the T1 and T2 aircraft. It is located on the pilot side of
the instrument panel and uses dc power. It is
protected by a 5 -ampere circuit breaker, placarded
TURN & SLIP PILOT, located on the overhead circuit
breaker panel. Refer to Figure 2-16, Sheet 4.
2-92. AIRSPEED INDICATORS.
Airspeed indicators are installed separately on
the pilot and copilot's sides of the instrument panel.
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 (260 KIAS,
0.52 mach) at the aircraft's present altitude.
