7.12 - Air Data System and Instruments
See
.
The airplane's air data system consists of:
-
Primary systems:
.
two separate static pressure systems,
.
two separate dynamic pressure systems.
-
An alternate static pressure system.
Static Pressure Systems
Primary Systems
Two dual static ports (one on each side of the fuselage tail section) supply a dual
system routed to the cockpit.
Static system 1 supplies:
-
ADC 1,
-
the standby instrument, through the Normal / Alternate static source
switching valve, when the ALTERNATE STATIC SOURCE selector is in the
Normal position (pushed). The ALTERNATE STATIC SOURCE selector is
located on the instrument panel under the right-side control wheel.
Static system 2 supplies ADC 2.
Each line has a drain plug located under the instrument panel on the right side.
Alternate Static Source
The alternate static port, located inside the rear fuselage, supplies a line routed to
the Normal / Alternate static source switching valve.
If a false airspeed indication or primary static system failure is suspected, the pilot
can pull the ALTERNATE STATIC SOURCE selector fully out to select the
alternate static source. In this case, static pressure from the alternate line is only
provided to the standby instrument. Static pressure from the alternate line is not
provided to either ADC.
Section 7
Description
Pilot's Information Manual
PIM TBM 960 - Edition 0
Rev. 00
Page 7.12.1
PIM - DO NOT USE FOR FLIGHT OPERATIONS
