Emergency Static Air Source System; Electrothermal Heated Windshield Segment - Beechcraft Baron G58 Pilot Operating Handbook

Section 3A
Abnormal Procedures

EMERGENCY STATIC AIR SOURCE SYSTEM

THE EMERGENCY STATIC AIR SOURCE SHOULD BE
USED FOR CONDITIONS ANYTIME THE NORMAL STATIC
SOURCE HAS BEEN OBSTRUCTED. When the airplane has
been exposed to moisture and/or icing conditions (especially
on the ground), the possibility of obstructed static ports should
be considered. Partial obstruction will result in the rate of climb
indication being sluggish during a climb or descent. Verification
of suspected obstruction is possible by switching to the emer-
gency system and noting a sudden sustained change in rate of
climb. This may be accompanied by abnormal indicated air-
speed and altitude changes beyond normal calibration differ-
ences.
Whenever any obstruction exists in the Normal Static Air Sys-
tem, or the Emergency Static Air System is desired for use:
1. Emergency Static Air Source . . . . . EMERGENCY (ON)
2. For Airspeed Calibration and Altimeter Correction, refer
to Section 5, PERFORMANCE.
When the Emergency Static Air System is no longer needed:
3. Emergency Static Air Source . . . . . . . . (NORMAL) OFF
ELECTROTHERMAL HEATED WINDSHIELD SEG-
MENT
Failure of the heated windshield segment can be confirmed by
cycling the WSHLD HEAT switch to OFF, then ON. If a deflec-
tion of the Alt Load is not apparent, consider the system inop-
erative and exit icing conditions. Partial windshield deicing may
be accomplished using the defroster. Maximum defrost heat is
achieved as follows:
1. Heater Switch . . . . . . . . . . . . . . . . . . . . . . . . . . HEATER
2. Cabin Air Control . . . . . . . . . . . . . . . . . . . . . . .PULL AFT
3A-12
(lower sidewall adjacent to pilot)
(not more than 1/2 travel)
Model G58
April, 2008