Standby Pitot-Static System Schematic (Figure 5-8) - BOMBARDIER LEARJET 40 Pilot's Manual

Pilot's Manual
Static 1 from the left probe connects with static 2 on the right probe to
provide static pressure to the pilot's ADC. Static 1 from the right probe
combines with static 2 on the left probe to provide static information to
the copilot's ADC. This crossover arrangement reduces system errors
(Figure 5-7).
A third pitot-static probe, mounted above the main probe on the right
side of the airplane, provides total and static pressure inputs to the
standby instrument group. Moisture drains are provided for the stand-
by pitot-static lines. The two drains for the standby pitot-static system
are flush mounted on the right side of the airplane just aft of the nose
wheel door. The main pitot-static probes are physically located at the
lowest point of the primary pitot-static system plumbing and therefore,
do not require moisture drains. The pitot source on the standby probe
provides total pressure to the standby Mach/airspeed indicator. There
are two static sources on the standby probe, one provides static infor-
mation to the standby altimeter and the other provides data to the
standby Mach/airspeed indicator (Figure 5-8).
STANDBY STATIC PRESSURE
STANDBY PITOT PRESSURE
STANDBY
MACH/AIRSPEED
INDICATOR
STANDBY
ALTIMETER
STANDBY PITOT-STATIC SYSTEM SCHEMATIC
5-34
Figure 5-8
STANDBY
PITOT/STATIC
PROBE
PITOT
STATIC 1
STATIC 2
PM-132A