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All of the mode annunciations and system / subcomponent failure
annunciations may be tested on the ground during preflight with the ST/R
switch (momentary) on the upper right of the heading display. This test
feature is wired through the nutcracker (squat) switch system to operate in
the ST or self-test mode on the ground and the R or reset mode in the air.
Pressing the ST/R button in the air will reset the heading indicator,
recapturing a primary or alternate heading source if one is available.
Pressing the ST/R button during a ground preflight will illuminate the mode
annunciations, display warning flags and indicate a DBDI malfunction by a
five (5) second flashing red STBY light followed by continuous illumination
of the light.
On airplanes having Aircraft Service Change (ASC) 217, DBDI MANUAL
STBY switches are installed on the outboard side of the pilot and copilot
forward instrument panels, one for each DBDI. The installation is shown in
Figure 5. (A switch that enables manual selection of the standby mode is
located on the face of the DBDI electronic module in the radio rack on
airplanes not having ASC 217). This switch allows the crew to manually
select the standby (STBY) heading mode in flight to crosscheck inertial
(IRS) heading information, compensate for faulty IRS information, or to
select a heading source during realignment of the IRSs.
3. Controls and Indications:
(See Figure 4 and Figure 5.)
A. Circuit Breakers (CBs):
Circuit Breaker Name CB Panel Location Power Source
STBY HORZN CP E-4 EMER 28V DC
DBDI #1 (SN 1212 & subs)
(DDRMI #1 on SN 1000-1211)
CP F-4 ESS 28V DC
DBDI #2 (SN 1212 & subs)
(DDRMI #2 on SN 1000-1211)
CP G-4 ESS 28V DC
E DBDI #1 (SN 1212 & subs)
(E DDRMI #1 on SN 1000-1211)
CP H-5 EMERG 28V DC 1C
E DBDI #2 (SN 1212 & subs)
(E DDRMI #2 on SN 1000-1211)
CP I-5 EMERG 28V DC 2B
4. Limitations:
There are no limitations for this system at the time of this revision.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-34-00
Page 15
October 11/01
Revision 5
Digital Bearing and Distance Indicator
Figure 4
OPERATING MANUAL
2A-34-00 PRODUCTION AIRCRAFT SYSTEMS
Page 16
October 11/01
Revision 5
DBDI MANUAL STBY Switch Installation
Figure 5
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-34-00
Page 17
October 11/01
Revision 5
2A-34-40: Radio Altimeter System
1. General Description:
The GIV is equipped with two independent AA-300 radio altimeters. Each has a
dedicated Receiver / Transmitter (R/T) unit, transmitting antenna and receiving
antenna. (Antenna location is shown in Figure 27.) There are no off / on controls
(switches) or separate displays for the radio altimeters. The radio altimeters
operate continuously when the airplane Main DC buses are powered, using high
resolution, short pulse radar signals that are accurate over wide variations of
terrain, target reflectivity, weather and airplane altitude.
The radio altimeters provide a continuous readout of airplane altitude above
ground level in the operating range of zero to twenty-five hundred (0-2,500) feet.
Accuracy of the altitude readout varies with height above ground, with readings
between zero and one hundred (0 and 100) feet accurate to within three (3) feet,
readings between one hundred and five hundred (100-500) feet have an accuracy
within three percent (3%), and readings between five hundred and twenty-five
hundred (500-2,500) feet accurate within four percent (4%). Above twenty-five
hundred (2,500) feet, the radio altimeters continue to operate, however the radio
altitude information is no longer displayed because of the increase in error margin
at higher altitudes.
2. System Operation:
Radio altimeter data is sent to the Data Acquisition Units (DAUs) to be digitized
and then forwarded over the Avionics Standard Communications Bus (ASCB) to
the symbol generators for display on the Primary Flight Display (PFD). A discrete
signal is also provided to the landing gear indication system to provide the altitude
warning at twelve hundred (1,200) feet if the landing gear is not down and locked
(see the discussion in Section 2A-32-30, Extension and Retraction System of this
manual).
The PFD displays of radio altitude differ slightly between airplanes with SPZ-8000
and SPZ-8400 Digital Automatic Flight Control Systems (DAFCS). See Figure 6
and Figure 7 for illustrations of the radio altitude display formats.
A. SPZ-8000 Radio Altimeter Display:
The display of radio altitude on the PFD is selected using the SENSOR
function on the Display Controller (DC). When SENSOR is selected, a
　
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