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the primary source for air data. The is a self contained unit incorporating
pressure sensing modules and all required processing and input/
output functions in a single unit. Each computer is independent of the
other and has independent circuit breakers.
The air data system provides the required airplane airspeed, air temperature,
altitude and vertical speed data for the Electronic Flight Instrument
System (EFIS) displays, Attitude and Heading Reference
System (AHRS), dual stall warning system, autopilot, transponders,
spoileron computer, cabin pressurization, Digital Electronic Engine
Control (DEEC) and landing gear warning system as required. The Air
Data System (ADS) accepts static air pressure, total air pressure, total
air temperature, various discrete signals and baro set inputs. The #1
and #2 ADCs receive power from the L and R ESS BUS respectively,
through ADC 1 and ADC 2 circuit breakers. The circuit breakers are located
on the pilot’s and copilot’s circuit breaker panels (INSTRUMENT/
INDICATIONS group).
ADC REVERSION
Display of the ADS data on the EFIS display is controlled by the pilot
or copilot via the ADC reversionary control switch (Figure 5-14). The
reversionary control panel, located below the EICAS display (DU#2),
incorporates an ADC reversion switch which has three positions, 1 -
ADC NORM - 2. In the ADC NORM position, the IC-600s receive air
data from their on-side ADC. In the “1 or 2” position both IC-600s receive
air data from the selected source. If the switch is not in the NORM
position, an annunciator of the selected source is displayed above and
to the left of the ADI on both PFDs.
Pilot’s Manual
5-36 PM-126A
STANDBY INSTRUMENTS
The standby instrument group (Figure 5-9) includes a barometric altimeter,
a airspeed/Mach indicator, an attitude indicator, mounted on the
center instrument panel above the CWP and RMUs. The standby instruments
have their own pitot-static probe to provide air data information.
The instruments are of traditional mechanical design. If a fault
occurs which causes one of the ADCs to output misleading information
to the PFDs, the standby instruments act as a useful comparison to indicate
which of the three displays is incorrect.
STANDBY INSTRUMENT GROUP
Figure 5-9
STANDBY ALTIMETER
The standby altimeter displays baro corrected altitude in a pointer/
counter drum display. The dial graduations are marked every 20 feet.
Above sea level the counter displays every 100 feet up to 55,000 feet of
operational range. The indicator has dual barometric correction, from
27.9 to 31 inches of mercury and 946 to 1050 hectoPascals. Back lighting
is provided by 5-vdc to illuminate the standby altimeter indicator at
night.
STANDBY AIRSPEED/MACH INDICATOR
The standby airspeed/Mach indicator provides indicated airspeed by
means of a pointer indicating against a 50- to 400-knot dial and a Mach
sub-dial ranging from 0.3 to 1.0 Mach. Maximum allowable airspeed
(Vmo) is indicated at 325 knots by a red radial mark on the airspeed dial.
Maximum allowable Mach (Mmo) is indicated at 0.75 Mach by a red
and white striped radial mark on the Mach sub-dial. Back lighting is
provided by 5-vdc to illuminate the standby airspeed/Mach indicator
at night.
2 2 0 0
0
40
35
30
25 20
16
14
12
10
6
G C
L
E
P
A
LU
TO
1013
2992
51,000 FT
VIB
ON
hPa
ALT
In Hg
0
9
8
7
6
5
4
3
1
2
Pilot’s Manual
PM-126A 5-37
STANDBY ATTITUDE INDICATOR
The standby attitude indicator provides a visual indication of the airplane
flight attitude. It is located in the center of the standby instrument
group (Figure 5-9) where it can be viewed easily by both pilots. It is
powered from the emergency battery bus so that it will remain powered
for at least one hour after the loss of airplane generator power. The
standby attitude indicator will continue to provide an accurate display
of aircraft attitude for a further nine minutes after the loss of all airplane
power.
The indicator is an electrically-driven gyro whose vertical attitude is
maintained by a mechanical erection system. The power warning flag
is pulled from view after the gyro has spun up to valid operating speed
and reappears if there is any interruption of source power or the unit is
in caged mode.
Back lighting is provided by 5-vdc to illuminate the standby attitude
indicator at night.
STANDBY COMPASS
　
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