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Revision 5
Circuit Breaker Name CB Panel Location Power Source
STBY PITOT HT CONT CP L-13 ESS 28V DC
STBY PITOT HT PWR CP M-13 ESS 115V AC φA
AOA PRB HTR #1 CP L-14 ESS 28V DC
AOA PRB HTR #2 CP M-14 MAIN 28V DC
DADC #1 CP F-3 ESS 28V DC
DADC #2 CP G-3 MAIN 28V DC
STBY AIR SPD IND CP H-4 (1) EMER 28V DC
DUAL MODE ALTM VIB CP H-3 (1) EMER 28V DC
STBY ALTM VIB CP H-3 (2) EMER 28V DC
DUAL MODE ALTM CP H-4 (3) ESS 28V DC
STBY ALTM VIB CP H-4 (4) EMER 28V DC
NOTE(S):
(1) SN 1000 -1059 (except 1001 and 1034) not having ASC 66
(2) SN 1000, 1002-1122 (except 1034) having ASC 66, SN 1001, and 1060
- 1167
(3) SN 1000, 1002 - 1059 (except 1034) not having ASC 66
(4) SN 1034, 1168 and subs
B. Caution (Amber) CAS Messages:
CAS Message Cause or Meaning
AOA HEAT 1-2 FAIL Angle of attack probe heater failed
L-R PITOT HT FAIL Indicated pitot tube heater elements not energized
SSEC DISABLED Static source error correction to DADC has been disabled
STBY PITOT HT FAIL Standby pitot heater elements not energized
TAT PROBE HT FAIL TAT probe heater has failed
C. Advisory (Blue) CAS Messages:
CAS Message Cause or Meaning
DADC 1-2 FAIL A DADC has failed
DADC MISCOMPARE The priority FGC has detected an unflagged miscompare
between DADC 1 and DADC 2
EPR 1 - DADC 2
EPR 2 - DADC 1
DADC malfunction has caused remaining DADC to supply
information to both EPR systems
4. Limitations:
There are no limitations to this system at the time of this revision.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-34-00
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Standby Flight Instruments
Figure 1
OPERATING MANUAL
2A-34-00 PRODUCTION AIRCRAFT SYSTEMS
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Revision 5
SAT / TAT Probe
Figure 2
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-34-00
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Revision 5
OPERATING MANUAL
THIS PAGE IS INTENTIONALLY LEFT BLANK.
2A-34-00 PRODUCTION AIRCRAFT SYSTEMS
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Pitot / Static System
Schematic
Figure 3
OPERATING MANUAL
2A-34-00
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October 11/01
2A-34-30: Attitude and Direction System
1. General Description
The standby attitude and direction systems provide references for steering the
airplane in the desired direction using basic instruments that remain powered
during instances of failure / malfunction of the Primary Flight Displays (PFDs) and
/ or the Flight Management System (FMS). The following subsystems, units and
components are included:
• Standby Attitude Indicator
• Standby Directional System
2. Description of Subsystems, Units and Components:
A. Standby Attitude Indicator:
The standby attitude indicator (shown in Figure 1) is a gyroscopically
driven artificial horizon that provides a backup indication of airplane pitch
and roll in the event of a failure or malfunction of PFDs, FMS or IRS
systems. The indicator contains a sphere divided into hemispheres painted
blue and brown (or black) representing sky and earth. Markings on the
hemispheres denote pitch attitude in five degree (5°) increments from level
up or down to eighty degrees (80°). When the airplane is initially powered,
the indicator will power-up and self-erect once the internal gyroscope
reaches operating speed. To immediately erect the indicator, use the cage
knob on the face of the instrument, orienting the sphere upright and
leveling the horizon (where the sky and earth representations meet). The
airplane symbol on the face of the instrument is adjusted to match the
airplane pitch attitude by rotating the cage knob.
At the top of the instrument is a triangular pointer that indicates airplane
bank angle against the semicircular scale surrounding the artificial horizon.
The scale is marked in ten degree (10°) increments up to thirty degrees
(30°) of bank, and additional marks at forty-five degrees (45°) (for Serial
Number (SN) 1330 and subsequent only), sixty degrees (60°) and ninety
degrees (90°).
The standby attitude indicator is powered by the Emergency DC bus. If
power to the instrument is interrupted, a red warning flag is displayed on
the face of the instrument (the flag is also displayed when the indicator is
caged). If Emergency DC bus power to the indicator is lost (battery
depleted - warning flag displayed) the rate of spin of the gyro may be
sufficient to supply attitude information for several minutes before
becoming unreliable.
On airplanes SN 1330 and subsequent, the standby attitude indicator has
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