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maintenance action. See Figure 9 and Figure 10. For additional information, refer
to Chapters 5 and 31 of the GIV Maintenance Manual.
2. Description of Subsystems, Units and Components:
The system is comprised of three major components:
• G-Meter Computer/Display
• Accelerometer
• G-Meter Fail Annunciator
A. G-Meter Computer/Display:
The G-meter computer (located in the right radio rack) retains the current
landing plus the previous seven (7) landings in non-volatile memory. The
recorded accelerations are read off the computer display.
The G-meter computer display provides the flight crew with a method to
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determine actual landing force encountered by the aircraft during the
previous eight touchdowns. It consists of a Light Emitting Diode (LED)
display, a DISPLAY ON/OFF switch and a MODE switch. These
components are shown and described in Figure 8.
B. Accelerometer:
The system accelerometer is installed in the center forward portion of the
wheel well at Fuselage Station 456.7. The accelerometer is capable of
measuring from -3.0 to +6.0 Gs.
C. G-Meter Fail Annunciator:
The G-meter fail annunciator is located in the right hand system monitor
panel above the right hand radio rack (incidentally shown in Figure 12).
The annunciator illuminates whenever the G-meter system loses power
and/or the system detects a fault.
3. Controls and indications:
See Figure 8.
A. Circuit Breakers (CBs):
Circuit Breaker Name: CB Panel: Location: Power Source:
G-METER CP C-13 ESS DC Bus
4. Operation:
With the radio rack cover removed, the G-meter computer is seen mounted on the
upper shelf of the right hand forward radio rack. When the DISPLAY SWITCH is
placed to ON, all display digits will illuminate while the unit preforms a self test.
After the self test is completed, the value for the most recent landing will be
displayed.
The display readout is arranged as follows; the digit to the left is the landing
number, 1 through 8, 1 being the most recent landing. The next 3 digits are the
gravity force (“G”) readings from -3.00 to +6.00 Gs.
Each time the MODE switch is momentarily placed in the MEM position, the next
landing’s value will be displayed in a last-in, first-out order, for the previous 8
landings.
The display can be reset by momentarily placing the MODE SWITCH in the RST
position. This action involves only internal and front panel gravity force
measurement as currently displayed and does not cause a reset of either the
microcomputer or in any way modify information stored in the Electronically
Erasable Programmable Read Only Memory (EEPROM).
5. Limitations:
A. Flight Manual Limitations:
There are no Flight Manual limitations for the ’G’ monitor system at the time
of this revision.
B. System Notes:
Use Figure 9 or Figure 10 and readings from the G-meter computer to
determine if hard landing or overweight landing inspections may be
required.
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G-Meter Computer Display
Figure 8
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’G’ Monitor/Airplane Gross Weight: SN 1214 & Subs, SN 1000-1213 With ASC 190
Figure 9
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’G’ Monitor/Airplane Gross Weight: SN 1000-1213 Without ASC 190
Figure 10
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2A-31-40: Central Warning System
1. General Description:
The Gulfstream IV central warning system provides the flight crew with indications
of equipment status, operating conditions requiring action or indications that a
system is in operation. Manual and automatic testing of the warning system
indicators and indicating circuitry is also provided. Display of critical data is
ensured through both automatic and manual reversionary features. Limited
provisions for manipulation of display data based on personal preference are also
included.
The central warning system is one of the many systems integrated into
Honeywell’s SPZ-8000 (or SPZ-8400) Digital Automatic Flight Control System and
as such cannot be adequately described in the space available here. For
comprehensive reference material on the central warning system, refer to
Honeywell’s SPZ-8000 (or SPZ-8400) Digital Automatic Flight Control System
　
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