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charged, the internal batteries can power the clocks for up to 30 days.
3. Controls and Indications:
(See Figure 1.)
A. Circuit Breakers (CBs):
Circuit Breaker Name: CB Panel: Location: Power Source:
CLOCK #1 CP H-14 EMER DC Bus 1A
CLOCK #2 CP I-14 EMER DC Bus 2C
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4. Limitations:
There are no Flight Manual limitations established for cockpit clocks system at the
time of this revision.
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Cockpit Clocks (Typical)
Figure 1
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2A-31-30: Flight Data Recording System
The Gulfstream IV flight data recording system provides a means to receive, process
and store airplane operational information. The stored information is then protected so
that it may later be retrieved for historical, investigative or decision-making purposes.
The flight data recording system is described in the following subsections within this
section:
• 2A-31-31: Flight Data Recorder System (airplanes Serial Number [SN] 1183 and
subsequent)
• 2A-31-32: ’G’ Monitor System (airplanes SN 1034, 1156 and subsequent and
airplanes SN 1000 through 1155 with Aircraft Service Change [ASC] 118)
2A-31-31: Flight Data Recorder System
1. General Description:
On airplanes SN 1183 and subsequent, a solid-state digital flight data recorder
system is incorporated to receive, process and record parameters relating to
airplane operation and store the data in a protected environment.
The Avionics Standard Communications Bus (ASCB) is the primary source of
airplane flight data for the flight data recorder system. Parameter data generated
by airplane systems or transducers (sensors) is transmitted to the recorder
system in digital ARINC 429 or analog/discrete signal format. The data is
converted to a common digital format for recording. All data acquisition and format
conversions are accomplished within the flight data acquisition unit, which then
transmits reformatted data to the flight data recorder, where it is stored until
erased.
The flight data recorder system consists of the following units and components:
• Flight Data Acquisition Unit
• Flight Data Recorder
• Underwater Locating Beacon
• Flight Data Recorder Impact Switch
• Flight Data Recorder Maintenance Ground Override Switch
• Flight Data Entry Panel
• Flight Data Recorder Switch Panel
2. Description of Subsystems, Units and Components:
A. Flight Data Acquisition Unit:
The flight data acquisition unit, located in the right hand radio rack, accepts
flight data information sent from the sensors listed below. It then processes
the data and sends it to the flight data recorder for recording. Sensors
providing input to the flight data acquisition unit are the:
• Triaxial accelerometer
• Left and right spoiler position sensors
• Left and right aileron position sensors
• Elevator position sensor
• Elevator trim tab position sensor
• Rudder position sensor
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• Flaps position sensor
There are three fault indicator lights on the front panel: CAUTION, DFDR
FAULT and FDAU FAULT. (See Figure 2.) The CAUTION indicator light is
not functional for the GIV flight data recorder system. The DFDR FAULT
indicator light is triggered by a malfunction in the flight data recorder
circuitry. The FDAU FAULT indicator light is triggered by the flight data
acquisition unit built-in test circuitry detecting a fault in the flight data
acquisition unit. If either DFDR FAULT or FDAU FAULT indicator light
comes on, it will be necessary to replace the flight data acquisition unit.
B. Flight Data Recorder:
The flight data recorder (Figure 3) records and stores digitized ASCB data.
Data can be retrieved to assist in reconstruction of events relevant to an
incident. The flight data recorder continuously records and retains data for
a minimum of the previous 25 hours of operation. With electrical power
removed, recorded data is retained for a minimum of two years. The flight
data recorder is located in the aft equipment (tail) compartment. It is
international orange in color for high visibility to aid in location.
ASC 423 is available for airplanes SN 1421 and subsequent requiring FAR
Part 135 certification. This ASC upgrades the digital flight data recorder,
　
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