dicated by failure flags and loss of air data on
t h e c o r r e s p o n d i n g P F D ( F i g u r e 1 6 - 4 3 ) .
Although there are no ADC failure CAS mes-
sages, flags and loss of air data or compara-
tor annunciations provide an alert to the
flightcrew that a problem exists with the ADC
system.
Under normal operation, the ADCs also pro-
vide air data to the AHRS, flight director/au-
t o p i l o t v e r t i c a l m o d e s , t r a n s p o n d e r s ,
spoileron computer, cabin pressurization,
landing gear warning system, stall warning
system and DEECs (Figure 16-22). Either
ADC can provide air data to most of the
above, but only the on-side ADC is connected
to the stall warning systems and DEECs. A
stall warning system will be non functional
if the corresponding ADC fails and the DEEC
will revert to engine sensors if the corre-
sponding ADC fails. An amber L or R ENG
CMPTR FAULT CAS will be displayed, but
the engine will continue to operate in auto-
matic mode with an ADC failure.
ADC Reversion
On the reversion panel, the ADC reversion
switch has three positions, labeled "1 - ADC
NORM - 2" (Figure 16-22). In the "ADC
NORM" position, the IC/SGs receive air data
from their on-side ADC. In the "1 or 2" posi-
tion both IC/SGs receive air data from the se-
lected ADC source. If the switch is not in the
NORM position, an annunciator of the se-
lected source is displayed above and to the left
of the ADI on both PFDs (Figure 16-32). If a
reversion ADC source is selected, the current
flight director vertical modes will drop off, but
can be re-engaged.
Air data information to the optional FMS(s)
is supplied via the IC-600 units.
ADC Power Source
The left and right (No.1 and 2) ADCs receive
power from the L and R essential busses re-
spectively, through ADC 1 and ADC 2 circuit
breakers (Figure 16-22). The circuit breakers
a r e l o c a t e d w i t h i n t h e I N S T RU M E N T /
INDICATlONS group of circuit breakers on the
pilot and copilot circuit breaker panels.
With a loss of electrical power to both ADCs
or, if both fail, all air data supplied EFIS dis-
plays become invalid, accompanied by ap-
propriate warning flags. The flightcrew will
then have to rely upon the standby instru-
ments. The cabin pressurization controller
also reverts to a manual mode and the other sys-
tems mentioned above will be affected.
ADC Test
A preflight check of the ADCs is accomplished
via the SYSTEM TEST switch located on the
front, left corner of the center pedestal. When
the ADC position is selected and the TEST
SYSTEM knob is depressed, both ADCs self-
test. A successful test is indicated by a red
"ADC TEST" appearing above and to the left
of the ADIs on both PFDs (Figure 16-35), the
“overspeed” voice message warning sounding,
and the following displayed on the PFD's:
• Overspeed voice message
• Red “ADC TEST” annunciates in upper
left corner of the PFDs
• Airspeed at 330 kts (red digits)
• Altitude at 1,000 feet
L E A R J E T 4 5
P I L O T T R A I N I N G M A N U A L
16-30
FOR TRAINING PURPOSES ONLY
FlightSafety
international
Figure 16-21. Standby Pitot-Static
System Drains