Section 7 Pilot’s Operating Handbook
Description of Airplane and Systems EXTRA 500
Note A combination of high altitude and low engine power setting
may produce a PNEUMATIC LOW annunciation. In that
case, the engine power setting must be increased.
7.20.d Cabin Air Distribution
Air, entering the cabin through the cabin inflow check valve in
the front pressure bulkhead can be directed to the windshield
dispensers for defogging, to the cockpit legroom dispenser or
both in any portion. The respective push-pull control is located
in the centre console (see
Figure 7-7). Pulling the control knob
directs the air to the windshield.
7.21 Cabin Pressurization Control System
The aircraft is standard equipped with a pressure cabin,
allowing operation up to altitudes of 25,000 feet. The max.
operational pressure difference of the cabin is 5.5 psid
(380 hPa). This pressure differential results in a cabin altitude of
7,950feet at the max. operating altitude (FL 250).
The cabin pressurization system consists of two independent
systems:
• The environmental bleed air system (inflow)
• The cabin pressurization control system (outflow)
7.21.a Pressurization System Description
Cabin pressure is regulated by controlling the airflow leaving
the cabin through the cabin control outflow valve installed in
the rear pressure dome.
The pressure regulation system consists of a cabin control
outflow valve, an unregulated safety valve, the cabin
pressurization and dump (
PRESS) switch (see Figure 7-5), the
cabin pressure controller (see
Figure 7-19), the landing gear
squat switch, two indicators, one for cabin altitude and
differential pressure and one for cabin rate-of-climb, and
pressure switches which activate the red CABIN PRESSURE
7-60 26. January 2011
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