MilViz Beechcraft Baron 55, Руководство по эксплуатации для пилотов

Страница: 135 / 139

BEECHCRAFT Baron B55
Version 1.0 – 15 May 2012
[135]
The emergency static air source is designed to provide a source of static pressure to the instruments
from inside the fuselage should the outside static air ports become blocked. An abnormal reading of the
instruments supplied with static air could indicate a restriction in the outside static air ports. A lever on
the lower sidewall adjacent to the pilot, is placarded OFF NORMAL, ON EMERGENCY. When it is desired
or required to use this alternate source of static air, select the ON EMERG ENCY position. To recognize
the need and procedures for the use of emergency static air, refer to EMERGENCY PROCEDURES.
Airspeed Calibrations and Altimeter Corrections charts are in the PERFORMCNCE section.
VACUUM SYSTEM
Suction for the vacuum-operated gyroscopic flight instruments is supplied by
two engine-driven vacuum pumps, interconnected to form a single system. If
either pump fails, check valves automatically close and the remaining pump
continues to operate all gyro instruments. A suction gage on the instrument
panel (figure 84) indicates the amount of suction in the vacuum system in
inches of mercury. Two red buttons on the gage serve as source failure
indicators, each for its respective side of the system.
STALL WARNING
A stall warning horn on the cabin forward bulk head sounds a warning signal while there is time for the
pilot to correct the attitude. The horn is triggered by a sensing vane on the leading edge of the left wing
and is effective in all flight attitudes and at all weights and airspeeds. Irregular and intermittent at first,
the warning signal will become steady as the airplane approaches a complete stall.
In icing conditions, stalling airspeeds should be expected to increase due to the distortion of the wing
airfoil when ice has accumulated on the airplane. For the same reason, stall warning devices tend to lose
their accuracy. The sensing vane is installed on a plate that can be electrically heated, preventing ice
from forming on the vane of the transducer. A switch on the pilot's subpanel, placarded PITOT HEAT,
supplies power to the heated pitot mast and to the heating plate at the stall warning transducer.
However, any accumulation of ice in the proximity of the stall warning vane reduces the probability of
accuracy in the stall warning system whether or not the vane itself is clear of ice. For this reason, it is
advisable to maintain an extra margin of airspeed above the stall speed.
ICE PROTECTION SYSTEMS
SURFACE DEICE SYSTEM
Deice boots bonded to the leading edges of the wings and the tail surfaces are operated by engine-
driven pump pressure. Compressed air, after passing through the pressure regulator, goes to the
distributor valve. When the deice system is not in operation, the distributor valve applies vacuum to the
boots to deflate and hold the boots flat against the surface. Then, when the deice system is operated,
the distributor valve changes from vacuum to pressure and the boots inflate. After the cycle is
completed, the valve returns to vacuum hold down.
The de-icing control switches are located on the left section of the pilot’s lower subpanel (figure 85). A
three-position, spring loaded switch, with a center OFF position, a MAN (manual) down position, and an
Figure 84