AEROPRAKT-22LS Pilot Operating Handbook
A22LS-POH-04
35
8.9 Full and static pressure system
This system supplies the full (dynamic) and static pressure of the outside air to the
instruments measuring the flight parameters: airspeed, rate of climb and altitude. The
system consists of the full and static pressure probe 1 and full 2 and static 3 pressure lines
connecting the probe to the instruments (see
). Full and static pressure lines have
joints 4 used to disconnect the lines when the left wing is removed during aircraft
disassembly.
The full and static pressure lines are connected to the airspeed indicator(s). Static
pressure for altimeter and vertical speed indicator is supplied from the cockpit.
Good condition of the full and static pressure system is important for correct measurement
of the flight parameters and therefore for flight safety. Pilots must take measures to keep the
system in good condition: protect the full and static pressure probe with a cover (marked
with a red "Remove before flight" flag) and inspect the probe and lines during the preflight
check to make sure that they are not damaged or blocked (by water, ice, dirt, etc.).
Fig. 12. Full and static pressure system
8.10 Electrical system
Electrical system of A-22LS serves for generation of electrical power and supplying it to
the onboard electrical consumers.
When engine is running (its RPM is above 1400), electrical power is generated by the
engine alternator, converted by a rectifier-regulator (located on the firewall) and is stored in
a 14V DC 19Ah battery, located behind the left pilot seat. The battery is supplying
electrical power to the consumers (engine starter, instruments, lights, etc.) through the
electrical cables of appropriate section (depending on the consumed current), switches
and fuses (located on the instrument panel). The fuses are required to protect the
electrical system and consumers from short circuit and must be of appropriate type and
size.
MASTER switch controls power supplies of all onboard consumers (except for the engine
ignition system and consumers with their own built-in power source, e.g. GPS) together
with the electrical switches for separate consumers. The engine ignition system may be
switched ON/OFF only with the ignition switches.
Electrical system wiring depends on the electrical equipment/instruments installed in the
aircraft and therefore has main and additional (optional) portions. The respective wiring
diagrams are shown on
Fig. 18.
