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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-27. Display Switching Panel

Figure 34-28. Display Brightness Panel

34-36 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

DISPLAY REVERSION NOTES

CONTROLLER (DRC)
The display reversion controller, mounted on
the overhead panel, provides manual control
of the DUs in case of malfunction or failure.
It has four display system control knobs la-
beled DU1, DU2, DU3, and DU4 from left to
right. The display system control knobs have
three positions: OFF, NORM, and ALT. The
MFD display switching knobs have two posi-
tions and are labeled NORM and PFD.

Dispatch with one display failed (DU3) is a

program requirement. In each failure case,
engine and CAS messages move to an alter-
nate display with CAS below the alternate en-
gine display page. If DU2 and DU3 should
both fail, engine display and CAS messages
will revert to the outboard 1/6 location of DU1
and DU4. The PFDs in that case would re-
main on DU1 and DU4, but the copilot would
have the ability to select the information to be
displayed in the outboard windows of DU4. If
DU1 should fail but no others, the PFD will
automatically revert to the DU2. The same
action would take place for DU4, which would
automatically revert the PFD to DU3.

Two 2-position switches are required for man-

ual display reversion (one for each pilot). The
manual reversion control panel allows for se-
lection of AGM/DU reversions. The AGM/DU
reversion switches are 3-position. The OFF po-
sition powers down its respective DU.

DISPLAY BRIGHTNESS PANEL

(DBP)
The display brightness control panel allows for
dimming and brightening of the DU displays.
It has two concentric knobs. The left knob as-
sembly is for DU1 and DU2. The right knob
assembly is for DU3 and DU4. These control
long-term display brightness.

FOR TRAINING PURPOSES ONLY 34-37

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-29. Display Units (DUs)

Figure 34-30. Display Unit Window Configurations

34-38 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

DISPLAY UNITS (DU) NOTES

The four display units provide the display of
information necessary to the flight crew for op-
eration of the aircraft. The displays are iden-
tified as pilot’s primary flight display (DU1),
pilot’s multi-function display (DU2), copi-
lot’s multifunction display (DU3) and copilot’s
primary flight display (DU4) from left to right
across the cockpit instrument panel.

The four DUs each incorporate a 14.1-inch

diagonal active matrix color LCD display. An
ambient light sensor to adjust short-term dis-
play brightness is mounted in the bezel. Each
DU has an input from a remote dimming knob
(DBP) to control long-term display bright-
ness, and two temperature controlled exhaust
fans (outlet on the back of the unit). The DUs
mount in a tray installed in the instrument
panel. Cam levers engage pawls in the tray to
aid with installation and removal.

Each of the four displays can be partitioned

into one or three sections of logically grouped
data called windows. The windows have pre-
defined sizes and locations. The pilot will be
able to select from a set of predetermined win-
dow configurations. The window configura-
tions and window content are selectable via
display controller menus and/or cursor control
of on-screen menus.

FOR TRAINING PURPOSES ONLY 34-39

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

DU NO. 1
15

DISPLAY
UNIT NO.1

L ESS

DU STATUS
BUS

L MAIN
DU NO. 2
HMG ON
DU STATUS
15 RELAY
BUS
DISPLAY
UNIT NO.2
PRI

MAU 1
15

DISPLAY
UNIT NO.2
SEC

DIMMING PANEL
L ESS
DU NO. 3
R MAIN

15
HMG ON
DISPLAY RELAY
UNIT NO.3
PRI

15

DISPLAY
UNIT NO.3 DU STATUS
SEC
BUS
R ESS DU NO. 4

DU STATUS
R ESS
BUS
MAU 2
15

DISPLAY
UNIT NO.4

Figure 34-31. DU Interface Diagram

34-40 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

The DUs communicate with the AGMs or a NOTES

mirrored DU over a high speed fibre channel
bus (3 inputs and 1 output). This data bus is
used to receive pixel data from the AGM or DU
repeater and to transmit pixel data on the DU
repeater. The DUs use an ARINC 429 bus for
status/wraparound back to the MAU.

The primary flight displays (PFD) provide all

attitude, altitude and heading information to
the flight crew. The multifunction displays
(MFD) provide the flight crew with situa-
tional awareness information and has the ca-
pability to display navigation chart
information, weather radar data, enhanced
ground proximity warning terrain data and
other sensor relational data relative to cur-
rent aircraft position.

FOR TRAINING PURPOSES ONLY 34-41

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-32. Primary Flight Display Window (PFD)

34-42 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

PRIMARY FLIGHT DISPLAY NOTES

WINDOW (PFD)
The PFD window displays information used
for tactical (short-term) control of the air-
craft. The default size on DU1 and DU4 is 2/3
size, but can be expanded to full screen.

Pilots may set the select ADI display window

parameters through display controller menus
only, by selecting the format they want to use
(2/3 or full display). Traditional or advanced
symbology set, ADI features and HSI attributes
are selected through the display controller
only. Desired symbology set or HSI map, plan
or compass can also be selected through the
display controller menus. HSI window selec-
tions or compass types, however, are the only
PFD parameters that can also be selected
through the CCD. The primary flight display
(PFD) window has the following features:

•TCAS targets added to HSI

•360-degree compass added to HSI
•Wind display added to HSI
•RNP/EPU readouts added to HSI
•3D effects increase usability
•Enhanced vertical speed display moved to
the right of the altitude tape
•Moving map added to HSI with the abil-
ity to display waypoints, navaids, and
airports

FOR TRAINING PURPOSES ONLY 34-43

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-33. I-NAV Illustration

34-44 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

INTEGRATED NAVIGATION • Enhanced integration of EGPWS

WINDOW (I-NAV) • Graphical flight planning
The I-NAV window provides the pilot several • Graphical radio tuning
advantages as a strategic navigational planning • Terrain on the vertical profile
tool. Typical missions include a large number
of pilot initiated changes to the flight plan • 3-D perspective view
along with the regularly occurring ATC initi-
• Terrain and obstacles
ated changes.
• Geopolitical information
Graphical flight planning aids decision mak-
ing for both pilot and ATC initiated flight plan • Airport maps
changes by increasing situational awareness
with the display of features such as terrain, po-
litical boundaries, airspace, navaids, airports, NOTES
and waypoints overlaid with TCAS and
weather radar.

The I-Nav window functions will be primar-

ily controlled via cursor control of on-screen
buttons/menus, however some selections will
be available via display controller menus.

The new features that the I-Nav window pro-

vides are as follows:

• Advanced layered map display

• Curved path transitions
• DME arcs
• Procedure turns
• Holding pattern icon
• VORs and NDBs
• Jet and Victor Airways (high and low alt)
• Airport symbols
• Runway orientation
• Approach, SID, and STAR
• Special use airspace
• Flight plan offsets
• Alternate flight plans
• Missed approach procedures
• Crossing points
• Performance data

FOR TRAINING PURPOSES ONLY 34-45

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-34. Primary Engine Instrument Window

Figure 34-35. Secondary Engine Instrument Window

34-46 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

PRIMARY ENGINE NOTES

INSTRUMENT WINDOW
The primary engine instrument window has
the following features:
• L/R EPR—analog dial, target, digital
readout, and associated annunciations
• L/R TGT—analog dial, digital readout,
and associated annunciations
• L/R LP—analog dial, digital readout,
and associated annunciations
• L/R HP—digital readout, and associ-
ated annunciations
• L/R Fuel Flow—digital readout and mis-
match indicator

SECONDARY ENGINE
INSTRUMENT WINDOW
The secondary engine instrument window 3-
D effects have been applied as necessary to in-
crease usability. The list of parameters is as
follows in digital readout only:

• L/R engine oil pressure

• L/R engine oil temperature
• L/R LP EVM
• L/R HP EVM
• L/R hydraulic pressure
• PTU hydraulic pressure
• AUX hydraulic pressure
• L/R fuel tank temperature
• L/R and total fuel quantity—digital read-
out and mismatch indicator

FOR TRAINING PURPOSES ONLY 34-47

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-36. Alternate Engine Display

Figure 34-37. Compacted Engine Display

34-48 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

ALTERNATE ENGINE DISPLAY NOTES

If the secondary engine instrument display is
not displayed on the DU with the primary en-
gine instrument display, then the primary en-
gine instrument display reverts to the alternate
primary engine instrument display, which re-
places the HP tachometer and FF displays
with L/R total fuel quantity digital readouts
and mismatch indicators

COMPACTED ENGINE DISPLAY

The compacted engine instrument display can
be selected to show a combination of primary
and secondary engine instruments on one dis-
play. The display consists of:

•EPR (same as the primary engine)

•TGT (digital readout only)
•LP (digital readout only)
•HP (digital readout only)
•FF (digital readout only)
•Oil pressure (digital readout only)
•Oil temperature (digital readout only)
•Fuel quantity (L/R and total digital read-
out only)

FOR TRAINING PURPOSES ONLY 34-49

34-50
AC POWER DC POWER DOORS SUMMARY

FOR TRAINING PURPOSES ONLY

HYDRAULICS ECS/PRESSURIZATION FUEL FLT CONTROL
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Figure 34-38. 2/3 Window Synoptic Illustrations

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

2/3 SYNOPTIC PAGE WINDOW

The 2/3 synoptic page window pages will be selectable via display controller menus or cursor
control of on-screen buttons/menus. The list of synoptic pages for PlaneView is as follows:

• AC Power • Hydraulics
• CMC • Summary
• DC Power • Uplinked Weather
• Doors • Video
• ECS/Press • Charts
• Flight Controls • NAV
• Fuel

Figure 34-39. Chart Window Illustration

FOR TRAINING PURPOSES ONLY 34-51

34-52
ALTERNATE ENGINE FLT CONTROL BRAKES BRAKES

FOR TRAINING PURPOSES ONLY

START GROUND SVC AC/DC ECS
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Figure 34-40. 1/6 Window Synoptic Illustrations (Sheet 1 of 2)

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

1/6 SYSTEM PAGE WINDOW

The 1/6 system page window system pages will be selectable via display controller menus or
cursor control of on-screen buttons. 3-D effects were applied to the system pages as necessary
to increase usability. The list of system pages for PlaneView is as follows:
•AC/DC Summary •Alternate Engine
•APU/Bleed •Compacted Engine
•Brakes •Engine Start
•CAS •Flight Controls
•Checklist •Ground Srvc Panel
•Datalink •TCAS
•ECS/Press Sum •Uplinked Weather
•Primary Engine •Video
•Secondary Engine •Waypoint List

R Engine Maintenance
R Essential TRU Fault
ADF 1 Fail
DME 1 Fail
L Generator Fail
L EPS Maintenance Reqd
Check CMC
Isolation Valve Open
EVS Maintenance Required
A/T 1-2 TQA Power Fail
Steer By Wire Off
L GCU Fail
External DC Available
External AC Available
CPCS Maintenance Required
APU Maintenance Required
APU Generator Maint Reqd

Figure 34-40. 1/6 Window Synoptic Illustrations (Sheet 2 of 2)

FOR TRAINING PURPOSES ONLY 34-53

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

SPEAKERS/ SPEAKERS/
HEADPHONES HEADPHONES

AUDIO AUDIO
CONTROL DIGITAL AUDIO BUS MRC DIGITAL AUDIO BUS CONTROL
PANEL PANEL

MASTER MASTER
ANNUNCIATOR ANNUNCIATOR
ASCB-D

BUTTON BUTTON
WARNING WARNING

CAUTION CAUTION

EICAS EICAS
FIBRE CHANNEL MAU FIBRE CHANNEL
DISPLAY DISPLAY

FROM OTHER FROM ENGINE SENSORS

ASCB-D ARINC 429 AND OTHER
AIRCRAFT SYSTEMS
AIRCRAFT SYSTEMS

Figure 34-41. Monitor Warning Diagram

34-54 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

MONITOR AND WARNING Subsystem Monitoring

FUNCTION (MWF) Subsystem monitoring is performed by the
The PlaneView system consists of two inde- monitor and warning function installed in the
pendent monitor warning functions and there- MAUs. Subsystem monitoring provides a num-
fore two CAS message logic processes. Crew ber of monitors that alert the pilot of unsafe
alerting and aural warnings are performed by or non-normal situations that may occur dur-
the monitor and warning function installed in ing flight. These monitors include:
the MAUs.
• Altitude alert monitor
• Engage monitors
Software/Hardware
Components of the MWF • Aircraft configuration monitor
•Monitor warning function • Autothrottle takeoff hold monitor
•Master warning/caution annunciators • Emergency descent mode
•Control I/Os (containing aural warning • Speed brake monitor
tone generator) • Category II monitors
MWF 1 is located in MAU 1 while MWF 2 is • Display unit wraparound monitors
located in MAU 2. The monitor warning func-
tions monitor the status of the different aircraft • Ground spoiler monitor
parameters and provide the crew with aircraft • Peak brake temperature monitor
status information. Both monitor warning
functions are active at the same time and out- • Rudder limit monitor
put their status on the ASCB. • G-Meter monitor

Crew Alerting System NOTE

The stall warning monitor is located
Crew alerting is performed by the monitor in the AFCS.
warning function (MWF). The CAS supplies
warning, caution and advisory messages that
show on the EICAS display. The CAS message
display area on the EICAS display has 17 lines
with 27 characters for each line. The charac-
ters are displayed in both upper and lower
case.

Aural Warnings
Aural warnings are performed by the monitor
and warning function installed in the MAUs.
The aural warning tones are computed by the
monitor and warning function and outputted
via the MAU Control I/O card.

FOR TRAINING PURPOSES ONLY 34-55

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-42. PlaneView System Display Units

34-56 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

DISPLAY WINDOW AUTOMATIC DISPLAY

MANAGEMENT REVERSION
If a display unit fails, the PlaneView system
normally detects the failure and automatically
POWER-UP DEFAULT switches the display window configuration to
ensure that primary flight, primary engine,
Power-Up Default on Batteries and CAS information remains displayed. The
Power-up default settings, when on battery following figures show the display window
power, are: configurations for automatic reversion when
the system detects one or more DU failures.
• DU1 with a 2/3 PFD and the upper 1/6
set to alternate engine and the lower 1/6
window set to CAS. NOTES
• DU2 blank
• DU3 blank
• DU4 with a 2/3 PDF and the upper 1/6
set to alternate engine and the lower 1/6
window set to CAS.
Power-Up Default on AC Power
Power-up default settings with an AC power
source are:

• DU1 with a 2/3 PDF and the upper 1/6

set to flight controls and the lower 1/6
window set to brakes
• DU2 with a 2/3 I-NAV and the upper
1/6 window set to primary engine in-
struments and the lower 1/6 window set
to secondary engine instruments
• DU3 with a 2/3 I-NAV and the upper
1/6 window set to CAS and the lower 1/6
window blank
• DU4 with a 2/3 PFD and the upper 1/6
set to flight controls and the lower 1/6
window set to brakes

FOR TRAINING PURPOSES ONLY 34-57

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

25.3 LP 25.3

Fuel Qty
12000 10000
22000

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

25.3 LP 25.3

Fuel Qty
12000 10000
22000

DU1 DU2 DU3 DU4

Figure 34-43. Other PFD Automatic Display Reversions (Sheet 1 of 3)

34-58 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

25.3 LP 25.3

Fuel Qty
12000 10000
22000

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

25.3 LP 25.3

Fuel Qty
12000 10000
22000

1.42 FLEX 1.42 1.42 FLEX 1.42

1.02 EPR 1.02 1.02 EPR 1.02
TO/GA TO/GA

451 TGT 451 451 TGT 451

25.3 LP 25.3 25.3 LP 25.3

Fuel Qty Fuel Qty

12000 10000 12000 10000
22000 22000

Ground Spoiler Unarm Ground Spoiler Unarm

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

25.3 LP 25.3

Fuel Qty
12000 10000
22000

DU1 DU2 DU3 DU4

Figure 34-43. Other PFD Automatic Display Reversions (Sheet 2 of 3)

FOR TRAINING PURPOSES ONLY 34-59

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

25.3 LP 25.3

Fuel Qty
12000 10000
22000

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

25.3 LP 25.3

Fuel Qty
12000 10000
22000

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

25.3 LP 25.3

Fuel Qty
12000 10000
22000

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

Gr

25.3 LP 25.3

Fuel Qty
12000 10000
22000

1.42 FLEX 1.42

1.02 EPR 1.02
TO/GA

451 TGT 451

25.3 LP 25.3

Fuel Qty
12000 10000
22000

Gr

DU1 DU2 DU3 DU4

Figure 34-43. Other PFD Automatic Display Reversions (Sheet 3 of 3)

34-60 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

NOTES NOTES

FOR TRAINING PURPOSES ONLY 34-61

 ARINC 429 SECONDARY TUNING

34-62
ASCB PRIMARY TUNING

MAU 1 MAU 2 MAU 3

MCDU 1 MCDU 2
MCDU 3

FOR TRAINING PURPOSES ONLY

GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

MRC 1 3rd NAV/COM MRC 2

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Figure 34-44. FMS/Radio Tuning Diagram

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

FLIGHT MANAGEMENT
SYSTEM (FMS )
The flight management system (FMS) pro- The FMS is a software function located on
vides control outputs to the autopilot system the processor (PROC) modules in the modu-
to fly the aircraft, both laterally and verti- lar avionics units (MAU). The software for
cally, along a planned route. The FMS provides FMS 1 is installed on PROC module No. 2 in
the electronic display system with flight plan MAU 1. The software for FMS 2 is installed
and status information to be displayed. on PROC module No. 3 in MAU 2. The soft-
ware for FMS 3 is installed on PROC module
The FMS helps the pilot with aircraft flight No. 6 in MAU 3.
planning, navigation, data base and redun-
dancy management. The FMS is capable of The FMS uses the following data:
managing flight details from aircraft takeoff
to touchdown. It is also capable of providing • Pilot data entries made during initial-
detailed predictions regarding estimated time ization
and fuel remaining along an entire flight plan. • Flight plan data (kept in memory)
With this information, the FMS can perform
high accuracy, long-range lateral and vertical • Data inputs to the FMS
navigation along a flight plan. The FMS com- • Inputs from other avionics systems
municates with a number of sensors to deter-
mine the most accurate aircraft position.

Figure 34-45. MCDU Display

FOR TRAINING PURPOSES ONLY 34-63

34-64
MRC 1 MRC 2
NIM 1 NIM 2
ASCB-D
TNIC PROC 1 IRU IRU IRU NIC PROC 3 IRU IRU IRU NIC PROC 5
NIC PROC 2 1 2 3 1 2 3
TNIC PROC 4 NIC PROC 6
CMC L ESS DC R ESS DC
AFCS LN A A429
A429 AFCS LN A

MAU 2
MAU 3

MAU 1
AFCS LN B AFCS LN B

CONTROL IO 1 CONTROL IO 2

A B A B A B
A422 A422
ANLG ANLG

FLIGHT
DISPLAY DISPLAY
GUIDANCE
CONTROLLER ANLG ANLG CONTROLLER
PANEL
1 2
L ESS DC R ESS DC

ANLG ANLG
ANLG ANLG ANLG ANLG
PILOT TCS CO-PILOT TCS

FOR TRAINING PURPOSES ONLY

PILOT PILOT SWITCH SWITCH CO-PILOT CO-PILOT
AUTO-PILOT PITCH TRIM
PITCH TRIM AUTO-PILOT
DISCONNECT SWITCH
A429 ELEVATOR A429 SWITCH DISCONNECT
ANLG TRIM SERVO ANLG

ANLG ELEVATOR ANLG

PITCH/TRIM
TRIM BRACKET
ENGAGE/
DISENGAGE ANLG
SWITCH
FLAP STAB
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

ANLG ANLG
CONTROLLER
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Figure 34-46. Autopilot Block Diagram

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

AUTOMATIC FLIGHT CONTROL steering commands presented on the PFD.

The AP and AT systems make up the subsys-
SYSTEM (AFCS ) tems to the autoflight system. The G450 uti-
The autoflight system functions as a com- lizes dual elevator and aileron servos.
pletely automatic flight control system
(AFCS). The AFCS is a dual system for both Automatic Pilot System
the autopilot (AP) and the autothrottle (AT)
subsystems. This is accomplished by hosting The AP system operates the flight controls of
each system in a different modular avionics the aircraft to keep a straight and level flight
unit. The purpose of the AFCS is to provide path in a set attitude and heading.
fail-operational flight director (FD), AP, yaw
damper and trim functions. The AT functions The AP system uses the avionics standard
are fail-passive. The autoflight system re- communication bus, version D (ASCB-D) to
ceives computed lateral (roll) and vertical interface with other systems. Mode indica-
(pitch) steering commands from the FD sys- tion data (armed and active modes) and pri-
tem for the autopilot and for display on the pri- mary flight display (PFD) selection are sent
mary flight display (PFD). In the event the AP on the ASCB-D to each PFD.
is disengaged, the pilot can manually fly the

Figure 34-47. Servo

FOR TRAINING PURPOSES ONLY 34-65

34-66
MRC 1 MRC 2
NIM 1 NIM 2
ASCB-D

TNIC PROC 1 NIC PROC 3 NIC PROC 5

NIC PROC 2 TNIC PROC 4 NIC PROC 6
CMC AFCS 2A
AFCS 1A AFCS 2B
AFCS 1B MAU 3

MAU 1
MAU 2
A429
ANLG

A B A B A B

ANLG

A429
ANLG

FOR TRAINING PURPOSES ONLY

TQA
LEFT RIGHT
ANLG ANLG
EEC EEC

R MN DC L MN DC
ANLG
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

FGP
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Figure 34-48. Autothrottle Block Diagram

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

AUTOTHROTTLE SYSTEM (A/T) NOTES

The A/T functionality resides inside the MAUs
and is part of the Automatic Flight Control
System. The A/T system automatically ad-
justs the throttle levers thus providing speed
control and thrust management for the air-
craft. The throttle quadrant incorporates two
separate integral servo loop channels to enable
control of each throttle individually. Each
channel has an ARINC 429 Rx, ARINC 429
Tx port, engage/disengage switch, go around
switch, and a disconnect switch that inter-
faces with the PlaneView equipment. The top
level PlaneView A/T changes are as follows:

• Add single engine A/T operation for all

modes except takeoff.
• Improved integration of the overspeed
protection between the AP and A/T.
• Improvements for cruise wave acivity
and any other problems identified with
the baseline SPZ-8500 system.

FOR TRAINING PURPOSES ONLY 34-67

34-68
MRC 1 MRC 2
NIM 1 NIM 2
ASCB-D

TNIC PROC 1 NIC PROC 3 NIC PROC 5

NIC PROC 2 TNIC PROC 4 NIC PROC 6
CMC DGIO 2 SGIO 5
DGIO 1 PROC 10 SGIO 6
SGIO 2
A429
PROC 8

MAU 3

MAU 1
MAU 2
WX
A B A B RT A A B

A429 A429
A429

FOR TRAINING PURPOSES ONLY

ADM ANLG ADM ANLG ADM
A429 1 2 3 A429

TAT TAT
L ESS DC R ESS DC L ESS DC
PROBE 1 PROBE 2
R EEC
L EEC
A429
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

CABIN PRESSURE
CONTROL UNIT
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Figure 34-49. Air Data Block Diagram

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

AIR DATA FUNCTION (ADF)

The primary purpose of the digital air data The ADM senses and transmits static and total
computing (DADC) system is to display air pressure to the ADA software. The ADA soft-
pressure, altitude and air temperature data on ware runs on top of the digital engine operat-
the primary flight displays (PFD). The pilot ing system platform, which is installed on the
and copilot use this air data for navigation. The processor card of the network interface con-
DADC system is also the primary source of air troller (NIC) interface processor module in
data for other avionics systems. The system each MAU. The NIC interface processor mod-
measures the pressure and temperature of the ule also receives total air temperature (TAT)
external ambient air and supplies this data to from external TAT probes and baro set inputs
the other systems. from the baro set control for barometric cor-
rection. The NIC interface processor module
The DADC system is a three air data module uses these data inputs to calculate the air data
(ADM) system that operates with three mod- parameters for use by other aircraft avionics
ular avionics units (MAUs) to process air data systems.
for other avionics systems. Each DADC sys-
tem uses a set of pressure probes, an ADM and
air data application (ADA) software.

Figure 34-50. Air Data Modules

FOR TRAINING PURPOSES ONLY 34-69

34-70
MRC 1 MRC 2
NIM 1 NIM 2
ASCB-D

TNIC PROC 1 NIC PROC 3 NIC PROC 5

ANT
NIC PROC 2 TNIC PROC 4 NIC PROC 6
CMC GPS 2 GPS 1
SGIO 3 SGIO 6

MAU 3

MAU 1
MAU 2
A B A B A B

A429
A429

A429

A429

FOR TRAINING PURPOSES ONLY

ANT

IRU IRU IRU

2 3
1
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL
international
FlightSafety

Figure 34-51. GPS Block Diagram

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

GLOBAL POSITIONING NOTES

SYSTEM (GPS)
The global positioning function (GPF) is used
to determine aircraft position from NAV-STAR
satellites and provides this position data to
the flight management system (FMS) and other
avionics systems as needed.

The GPS module supplies data to the FMS for

flight guidance and other information for var-
ious phases of flight.

The G350/G450 GPS consists of two GPS re-

ceivers (modules) installed in MAUs and two
passive antennae located forward on the air-
craft's fuselage.

The GPS module is a stand-alone receiver.

The GPS module utilizes the C/A (coarse ac-
quisition) code of the NAVSTAR (Navigation
and Signal Timing and Ranging) GPS satellite
constellation. The NAVSTAR GPS constel-
lation consists of 24 active satellites with 4
spare. The satellites orbit in six planes pro-
viding worldwide coverage. The GPS module
tracks the RF signal received from the active
antenna, determines the signal code phase and
carrier phase, computes the antenna position
and outputs the satellite position, pseudo
range, and delta range information for use in
hybrid computations. This data is output to the
inertials that are GPS Hybrid capable. The
antenna position provides the primary means
for aircraft navigation as utilized by the air-
craft avionics.

FOR TRAINING PURPOSES ONLY 34-71

34-72
MRC 1 MRC 2
NIM 1 NIM 2
ASCB-D

TNIC PROC 1 NIC PROC 3 NIC PROC 5

NIC PROC 2 TNIC PROC 4 NIC PROC 6
CMC DGIO 2 SGIO 5
AFCS 1 B AFCS 2 B SGIO 6
DGIO 1

MAU 3

MAU 1
MAU 2
A B A B A B

A429

ANLG IRS MSP ANLG

A429 A429

A429 A429
IRS IRS IRS
A429 A429

FOR TRAINING PURPOSES ONLY

1 2 3
A429
A429
APM APM APM

L ESS DC R MN DC L MN DC
L EMER ELT R EMER
BATT BATT
ANTISKID WX RTA
CONTROL
(G550) SDU EBDI NWS ECM
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL
international
FlightSafety

Figure 34-52. IRS Block Diagram

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

LASEREF V INERTIAL put (I/O) or a GPS module. The IRUs receive

air data system (ADS) altitude, altitude rate,
REFERENCE UNIT (IRU) and true airspeed inputs from MAU modules.
The IRS supplies inertial reference (IR) data From these measurements and inputs, the IRUs
to the flight management system (FMS), au- continuously calculate and output body frame,
tomatic flight control system (AFCS) and the local level frame, and earth frame parame-
flight data recorder system. The IRS also sup- ters.
plies ground speed, position and track, wind
speed and direction and attitude data to the The primary I/O interface of the LASEREF V
electronic display system (EDS). The EDS is ARINC 429; there is no ASCB interface. The
displays this data on the display units for the LASEREF V including the tray and configu-
pilot and copilot. ration module weighs only 11 lbs. It has a
front-mounted 55-pin circular connector.
The PlaneView IRS system consists of three
LASEREF V’s, three mounting trays and three The LASEREF V requires a small mounting
IM-950 configuration modules. tray which has non-critical installation align-
ment requirements due to the use of a PC based
The IRUs receive system initialization, air tray alignment procedure and storage of the
data, and GPS inputs on its ARINC 429 high— program generated tray alignment errors in
speed input buses. They also receive latitude the IM-950 configuration module. The
and longitude data for system initialization LASEREF V is passively cooled and no tray
from a modular avionics unit (MAU) input/out- mounted cooling fan is required.

Figure 34-53. Inertial Reference Unit

FOR TRAINING PURPOSES ONLY 34-73

34-74
MAU 1
RAD ALT NO. 1

ARINC 552
L MAIN
28 VDC

"SELF TEST" TCAS IA

Replace TCAS CU if ONLY the red 'TCAS FAIL' PASS DISP
lamp is on during any status display (following
the lamp test). When additional lamps are on, TCAS RA
correct indicated subsystem PRIOR to FAIL
replacement of TCAS CU.
DISP
TOP RAD
Honeywell International Inc. RT - 951 ANT ALT
TCAS COMPUTER
BOT XPDR
HARDWARE SOFTWARE
P/N 7517900- 55 004 DO-1716
ANT BUS
LEVEL B
S/N 01024111 S/W MOD
WT 14.2 Lbs A B C D E F G H HDG ATT
DATE INSP # JKLMNPRS
0201 29346 T U V W Y Z AA
AB AC AD AE AF DATA LOADER
AG AH AJ AK AL
PUSH
xx-xxx xxx xxxxx xxxx xx
xxxxxxxxxxxxxxxxxx AM AN AP AR AS TO
xxx-xxx
xxxx-xxx TSO C119b TEST TCAS
H/W MOD
D E F G H J K L M N P R S T U
V W Y A AA AB AC AD AE AF AG AH AJ
AK AL AM AN AP AR AS AT AU AV AW AY
Commercial xxxxx Systems Phoenix, AZ U.S.A.

RAD ALT NO. 2

MAU 2

ARINC 552

FOR TRAINING PURPOSES ONLY

R MAIN
28 VDC
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL
international

Figure 34-54. RAD ALT Block Diagram

FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

RADIO ALTIMETER SYSTEM NOTES

The radio altitude system calculates aircraft
altitude above ground level (AGL) during the
approach and landing phases of the flight.

Radio altitude data is shown on the primary

flight displays (PFD).

The radio altitude system operates over large

differences in terrain, weather conditions and
aircraft attitude to calculate aircraft altitude
during approach and landing. The system has
a maximum range of 2500 feet of altitude. The
PFD show the aircraft radio altitude as a dig-
ital display in the lower portion of the attitude
director indicator (ADI) sphere. The radio al-
titude system also supplies the decision height
(DH) output. The DH output sets the gain for
the localizer and glide slope signals for the
flight director. The DH range is from –20 to
2500 feet and is shown on the PFD.

Figure 34-55. Radio Altimeter

FOR TRAINING PURPOSES ONLY 34-75

 TOP
MRC 1 MRC 2 ANT

34-76
RADIO ALTIMETER 1

RADIO ALTIMETER 2

"SELF TEST" TCAS IA

Replace TCAS CU if ONLY the red 'TCAS FAIL' PASS DISP
lamp is on during any status display (following
the lamp test). When additional lamps are on, TCAS RA
correct indicated subsystem PRIOR to FAIL
replacement of TCAS CU.
DISP
TOP RAD
Honeywell International Inc. RT - 951 ANT ALT
TCAS COMPUTER
BOT XPDR
HARDWARE SOFTWARE
P/N 7517900- 55 004 DO-1716
ANT BUS
LEVEL B
S/N 01024111 S/W MOD
WT 14.2 Lbs A B C D E F G H HDG ATT
DATE
0201
INSP #
29346
JKLMNPRS
T U V W Y Z AA
AIR
AB AC AD AE AF DATA LOADER
AG AH AJ AK AL
PUSH
xx-xxx xxx xxxxx xxxx xx
xxxxxxxxxxxxxxxxxx AM AN AP AR AS TO
xxx-xxx
xxxx-xxx TSO C119b TEST
H/W MOD
D E F G H J K L M N P R S T U
V W Y A AA AB AC AD AE AF AG AH AJ
AK AL AM AN AP AR AS AT AU AV AW AY
Commercial xxxxx Systems Phoenix, AZ U.S.A.
GND
CWOW

DISPLAY CONTROLLERS 1 & 2

TCAS
CB

TCAS CPU

FOR TRAINING PURPOSES ONLY

GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

BOTTOM
international

MAU 1 MAU 2 MAU 3

ANT
FlightSafety

Figure 34-56. TCAS Block Diagram

 FlightSafety
international

GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

TRAFFIC ALERT AND regulatory changes anticipated to TCAS and

to implement enhanced features.
COLLISION AVOIDANCE
SYSTEM (TCAS) Provisions are made to accommodate the fol-
The traffic alert and collision avoidance sys- lowing future functionality:
tem (TCAS) is an auxiliary air traffic control
system. The system operates with Mode S Air • Increased receiver sensitivity to allow
for Mode S equipped aircraft to increase
Tr a f f i c C o n t r o l R a d a r B e a c o n S y s t e m the detection range to 100 nmi. This al-
(ATCRBS) (i.e., Mode A, Mode C) transpon- lows for the reception and processing of
ders. The TCAS finds the range, altitude and GPS data from other aircraft for the pur-
bearing of other aircraft equipped with pose of implementing CNS/ATM func-
ATCRBS transponders in relation to the lo- tions, as well as providing a longer range
cation of its own aircraft. Communication for display of TCAS traffic.
with another TCAS equipped aircraft is sup-
plied by the onboard transponders. • As part of the Change 7 upgrade, the al-
titude alerter function will reduce un-
The TCAS-2000 installation on PlaneView necessary resolution advisories (RAs).
incorporates a single directional antenna and • Flight identification for intruder air-
a single L-band antenna, and precise match- craft will be available for display as an
ing of coaxial cable lengths is required. The upgrade to support CNS/ATM.
TCAS-2000 has been designed to provide for

"SELF TEST" TCAS IA

Replace TCAS CU if ONLY the red 'TCAS FAIL' PASS DISP
lamp is on during any status display (following
the lamp test). When additional lamps are on, TCAS RA
correct indicated subsystem PRIOR to
replacement of TCAS CU.
FAIL DISP
TOP RAD
Honeywell International Inc. RT - 951 ANT ALT
TCAS COMPUTER
BOT XPDR
HARDWARE SOFTWARE
004 DO-1716
ANT BUS
P/N 7517900- 55
LEVEL B
S/N 01024111 S/W MOD
WT 14.2 Lbs ABCDEFGH
HDG ATT
DATE INSP # JKLMNPRS
0201 29346 T U V W Y Z AA
DATA LOADER
AB AC AD AE AF
AG AH AJ AK AL
PUSH
xx-xxx xxx xxxxx xxxx xx
xxxxxxxxxxxxxxxxxx AM AN AP AR AS TO
xxx-xxx
xxxx-xxx TSO C119b TEST
H/W MOD
D E F G H J K L M N P R S T U
V W Y A AA AB AC AD AE AF AG AH AJ
AK AL AM AN AP AR AS AT AU AV AW AY
Commercial xxxxx Systems Phoenix, AZ U.S.A.

Figure 34-57. TCAS CPU

FOR TRAINING PURPOSES ONLY 34-77

 AGM NO. 1 (MAU 3) AGM NO. 4 (MAU 1)

34-78
EGPWM 1 (MAU 3) EGPWM 2 (MAU 2)

FOR TRAINING PURPOSES ONLY

AGM NO. 2 (MAU 3)
AGM NO. 3 (MAU 2)
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL
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FlightSafety

Figure 34-58. EGPWS Block Diagram

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

ENHANCED GROUND The EGPWS uses precise aircraft position in-

formation and an on-board world terrain map
PROXIMITY WARNING SYSTEM database to provide much earlier ‘predictive’
(EGPWS) warnings than the typical GPWS warnings.
The enhanced ground proximity warning sys- Threatening terrain is visually displayed on the
tem (EGPWS) is an enhanced version of navigation displays.
GPWS. EGPWS enhances aircraft safety by
preventing controlled flight into terrain (CFIT) The EGPWS has seven operational modes de-
or controlled flight into water (CFIW) and in- signed to elevate crew awareness based on
creases the terrain awareness of the flight crew. phase of flight. Aural and visual alerts and
warnings are presented for unsafe proximity
EGPWS is an early warning system that alerts to terrain (ground proximity warning or GPW),
pilots of impending controlled flight into ter- deviation below ILS glideslope, excessive
rain by monitoring aircraft altitude, horizon- bank angle, altitude awareness call-outs, onset
tal and vertical speeds and flight modes of severe windshear and enhanced terrain
(takeoff, cruise, landing). Through this mon- awareness.
itoring EGPWS determines whether the air-
craft should be in the current situation, and The GPWS supplies the AGM data to use in
alerts the crew with visual and aural warn- displaying mode annunciation and terrain dis-
ings if a CFIT situation is imminent. The play on the PFD and MFD.
EGPWS computer integrates existing on-board
sensor data to predict CFIT situations. Voice
messages and advisory warnings identify spe-
cific CFIT conditions.

Figure 34-59. EGPWS Threatening Terrain Display

FOR TRAINING PURPOSES ONLY 34-79

 IRU NO. 1

34-80
R MAIN
28 VDC
10 AMP
1 AMP
L MAIN
MAU 1 28 VDC
WX NO.1 WX 884
DATA WX NO.1
CONTROLLER NO.1
CONT. BUS
IRU NO. 1
DATA WX NO.1
CONT.

WX NO.1
WX-880 DATA
MAU 2 COCKPIT
RTA WX NO.1
RANGE CONT. LIGHTING
WX NO.2 AIR OVHD/PED
CONT. CWOW

GND
CMC
DATA CROSS-SIDE
OFF
AIR (SLAVE)
DATA WX NO.2
RANGE CONT.
MAU 3

WX NO.2

FOR TRAINING PURPOSES ONLY

IRU NO. 2 DATA
DATA

WX NO.2
WX 884
CONT. BUS
CONTROLLER NO.2
1 AMP
WX NO.2 REMOTE ON R MAIN
28 VDC
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

IRU NO. 2
international

Figure 34-60. Weather Radar Block Diagram

FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

WEATHER RADAR
The primary purpose of the P880 Weather The dual weather radar controllers (WCs) in-
Radar System is to detect storms along the cludes knobs for WX gain, mode, range, tilt,
flightpath and give the pilot a visual color in- and brightness and push-buttons for TGT,
dication of their rainfall intensity and turbu- RCT, STAB, and TRB modes. Each WC also
lence content. After proper evaluation, the contains a lighted slave annunciator.
pilot can chart a course to avoid storm
areas.The weather radar power output is 10kW The RTA incorporates an 24-inch flat plate an-
nominal, 12kW maximum. The range is tenna, scan switch, transmit switch, and con-
2.5–300 nmi. Weather indications are dis- tains all the circuitry required for transmitting,
played on the multi-function display (MFD) receiving, signal processing, scan conversion,
and PFD, if selected. Storm intensity levels are serial data, and control interface to other sys-
displayed in bright colors contrasted against tem components as well as the EDS.
a deep black background. Areas of heaviest
rainfall appear in magenta, next rainfall ap-
pears in red, rainfall of medium intensity ap-
pears yellow, and areas of weakest rainfall
appear in green.

Figure 34-61. Weather Radar Components

FOR TRAINING PURPOSES ONLY 34-81

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REER GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-62. MRC Locations

MRC 2

MRC 1
LEER

34-82 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

DIGITAL MODULAR RADIOS

The PlaneView radio system consists of Contained within the MRC is non-volatile
Honeywell digital radios contained in two memory used to store radio and audio con-
modular radio cabinets, with a third stand- figuration information. Configuration data is
alone VHF digital Nav/Com. entered by means of the CMC for radio con-
figuration data and the AV-900 for the audio
configuration.
Modular Radio Cabinet (MRC)
The modular radio cabinet (MRC) consists of The MRC is mounted on an avionics shelf that
an ADF, DME, Mode S transponder (XPDR), has a cooling cutout for the NIM module air
network interface module (NIM), VHF data intake. No mounting tray is required. The unit
radio (VDR), and VOR/ILS/VDL (VIDL). mounts using a rear wedge and front mounted
Each of the functions is contained in a line re- swing bolts. The MRC uses front mounted
placeable module that is self-contained within connectors (D-Sub, BNC, TNC, and Triax).
its own housing and has its own power supply.
Two MRCs are used in the PlaneView system. The MRC contains two rear mounted cooling
fans, which are controlled by the modules.
The MRC provides radio audio and data re- Sensors within each module will enable fan op-
dundancy. Two independent audio circuits eration if the internal temperature exceeds a
contained in the MRC NIM provide audio re- preset limit. This allows the fans to be oper-
dundancy. Two independent paths, ASCB or ated only when the units need cooling. The air
ARINC 429 accomplish radio data redundancy intake is from the front (bottom for the NIM)
for the VDR, VIDL, and XPDR. and exhaust is out the rear.

Figure 34-63. Modular Radio Cabinet

FOR TRAINING PURPOSES ONLY 34-83

 ARINC 429 SECONDARY TUNING
ASCB PRIMARY TUNING

34-84
MAU 1 MAU 2 MAU 3

MCDU 1 MCDU 2
MCDU 3

FOR TRAINING PURPOSES ONLY

GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

MRC 1 3rd NAV/COM MRC 2

international
FlightSafety

Figure 34-64. MCDU Radio Tuning Block Diagram

 FlightSafety
international

GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

NETWORK INTERFACE
MODULE (NIM)
The network interface module (NIM) provides With Cert. Delta, radio tuning is accomplished
the interface between the MRC and the rest of on the MCDU, or CCD manipulating radio
the PlaneView avionics. data on the MFD. The primary tuning data
path is ARINC 429 from the MCDU to the
The NIM contains two independent audio pro- MAU then ASCB to the MRC NIM. The MRC
cessing functions for redundancy. Each audio NIM translates the ASCB data to RCB to com-
function receives all audio signals from the municate with each radio module. A secondary
radio modules contained within or connected to path is ARINC 429 directly between the MAU
the MRC. This audio data is converted to a dig- and the VDR (voice data radio), VIDL
ital audio bus output. Each digital audio bus out- (VOR/ILS/data link radio), and XPDR. For op-
put is connected to all audio panels. Other radio eration on emergency batteries (back-up
systems such as 3rd NAV/COM or HF radios can mode), MCDU 3 provides an ARINC 429 in-
input their analog audio into the NIM for trans- terface directly to the VDR 1, VIDL 1, and
mission on the digital audio bus. XPDR 1.

Figure 34-65. Network Interface Module

FOR TRAINING PURPOSES ONLY 34-85

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-66. NAV/COM Location

34-86 FOR TRAINING PURPOSES ONLY

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

NAV/COM RADIO NOTES

The NAV/COM is a stand-alone unit, which
contains the functionality of the VDR and
VIDL modules. This unit communicates with
the PlaneView avionics via ARINC 429 and
ties into the digital audio bus through the
MRC NIM.

FOR TRAINING PURPOSES ONLY 34-87

 34-88
HF NO. 1 HF NO. 2
MOMM XCVR MOMM XCVR
ARINC 429 HF 429 OUT
AUDIO
ARINC 429 HF 429 IN XCVR A PITT

XCVR A PITT HF 429 IN ARINC 429

HF 429 OUT ARINC 429

AUDIO
RF COAX RF COAX
RF IN/OUT
RF IN/OUT BACKPLANE
FIBER OPTIC IN RF IN/OUT
FIBER OPTIC IN
FIBER OPTIC OUT
FIBER OPTIC OUT 25 25
28 VDC PWR IN 28 VDC PWR IN HF DUAL MAU TUNING MRC RADIO
ASC8 TUNING
L IM IN R IM IN COUPLER
28 VDC 28 VDC MOUNT HF 429 OUT ARINC 429
NIC
+28 VDC PWR IN
HF 429 IN ARINC 429
RF IN/OUT ARINC 429 MCDU INPUT
AUDIO
HF ANTENNA HF ANTENNA
ARINC 429 MCDU OUTPUT
COUPLER NO. 1 COUPLER NO. 2
XCVR A PTT CONTROL I/O
FIBER OPTIC IN FIBER OPTIC IN
FIBER OPTIC OUT 3 3 FIBER OPTIC OUT
MCDU INPUT
ASC8 MAUTUNING RF IN/OUT 28 VDC IN 28 VDC IN RF IN/OUT HF SHUNT
NIM 28 VDC EXT ELEM PWR 28 VDC EXT ELEM PWR ANTENNA ARINC 429 MCDU OUTPUT
DUAL +28 VDC IN DUAL +28 VDC IN
MRC NO. 1 4
MISC DISCRETES MISC DISCRETES MCDU 2
RF IN/OUT RF IN/OUT
RF
ASC8 FEED
XRVR A PTT
BACKPLANE RF
FEED AUDIO
ASC8

MCDU OUTPUT ARINC 429 MRC RADIO ASC8

MAU TUNING
TUNING MAU TUNING ASC8

FOR TRAINING PURPOSES ONLY

BACKPLANE NIM
MCDU INPUT
NIC
MCDU OUTPUT MRC NO. 2
ARINC 429
MRC RADIO
MCDU OUTPUT
MCDU 1 TUNING
ARINC 429 MCDU INPUT MAU TUNING ASC8 ASC8

MCDU INPUT
NIC
ARINC 429 HF 429 OUT MCDU OUTPUT
MCDU 3
ARINC 429 HF 429 IN ARINC 429 MCDU INPUT

CONTROL I/O MAU NO. 3

CONTROL I/O MAU NO. 1
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL
international

Figure 34-67. High Frequency Block Diagram

Created by 1018
04-20-2004
RR07780 34-65
TECH CHECK
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

HIGH FREQUENCY RADIO (HF) The dual coupler mount connects both HF an-
tenna coupler units to the single shunt an-
The Collins HF-9000 communication system tenna using a copper bus bar.
provides long range voice and data commu-
nication capabilities to and from the aircraft. The shunt antenna is an integrated airframe
It is further divided into the HF No. 1 system component mounted in the leading edge of
and the HF No. 2 system. Each system consists the vertical stabilizer. The antenna element is
of an HF transceiver and an associated coupler fed from the dual coupler mount through the
unit utilizing a shared antenna. copper bus bar. It is electrically tied into air-
craft structure at the top, enabling entire air-
The HF No. 1 and No. 2 systems can be con- craft to act as a HF antenna.
trolled by any of the three MCDUs, using the
ARINC 429 digital data bus. All HF audio sig-
nal information is relayed to and from the air- NOTES
craft audio system through the NIM. With Cert.
Delta, any faults or failures are transmitted to
the CMC. In addition to their normal operation,
each HF system has an output for SELCAL.
Operating modes for the HF system (Simplex
and Half-duplex) are as follows:

• Upper Side Band (USB)

• Lower Side Band (LSB)
• Emergency (6 channels)
• Amplitude Modulation Equivalent
(AME)
• Radiotelephone Network (179 chs)
• I n t e r n a t i o n a l Te l e c o m m u n i c a t i o n s
Union (ITU) Maritime
Each of the two HF transceivers provide 99
u s e r- p r o g r a m m a b l e p r e s e t c h a n n e l s a n d
280,000 discrete operating frequencies cov-
ering 2.0000–29.9999 MHz range in 100 Hz
increments with selectable RF output power
levels of up to 175 watts peak (50 watts aver-
age). In addition, the six emergency channels
and 249 ITU Maritime Radiotelephone
Network channels are stored in nonvolatile
memory.

The two HF coupler units provide an interface

with their respective transceivers, and are de-
signed to match the impedance of the HF shunt
antenna. The transceivers sends control sig-
nals to, and receives feedback information
from, the antenna coupler units by a fiber optic
path connection.

FOR TRAINING PURPOSES ONLY 34-89

34-90
PILOT COPILOT
CCD PILOT COPILOT CCD
YOKE YOKE

MRC 1 MRC 2

PILOT
JACK
PANEL
COPILOT
PILOT JACK PANEL
ACB
CB COPILOT
ACP 1 ACP 2 ACB
CB

PILOT
SPEAKER COPILOT
PILOT O2 MASK
O2 MASK

APU HORN

FOR TRAINING PURPOSES ONLY

OB SERVER COPILOT
ACP SPEAKER
CVR

OBSERVER
ACP CB CABIN
FORWARD AND TALL SPEAKERS
SWITCH PANELS
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

OB SERVER
JACK PANEL
OBSERVER
international

O2 MASK
FlightSafety

Figure 34-68. Audio Block Diagram

 FlightSafety
international

GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

AV-900 AUDIO SYSTEM as the HF Comm.) and places it on the digital

audio bus. The AV-900 audio panels digitize
The audio system connects the communication the microphone inputs for transmission over
and navigation radios to the radio headsets, mi- the digital MIC bus. The MRC NIMs and all
crophones (MICs) and loudspeakers in the three audio panels then receive this informa-
aircraft. tion (via the digital MIC and audio buses).
There are three audio control panels on the air- Audio system adjustments required for each
craft. The number one audio panel (pilot side) aircraft are stored in nonvolatile memory. The
is powered by the aircraft’s left emergency AV-900 provides ten transmitter selections,
28 VDC bus. The number two and three audio twenty additional audio selection buttons,
panels (copilot and observer sides respec- emergency volume control, MIC volume con-
tively) are powered by the aircraft’s right es- trol, LCD display, volume control, and audio
sential 28 VDC bus. inputs.
The audio system consists of audio panels, The AV-900 also provides basic telephone op-
speakers, microphone switches, headphone eration to allow call pick-up, hang-up, hold,
jacks, hand microphone jacks, control col- transfer, and conference. Telephone dialing is
umn microphone jacks, mask microphone provided by the MCDU.
jacks, boom microphone jacks, and mainte-
nance-combination microphone/headphone The SELCAL functionality is integrated into
jacks located in the nose section and tail sec- the AV-900 audio system. In addition to inte-
tion of the aircraft. grating SELCAL into the AV-900, proper an-
nunciation is provided by the display system.
The MRC NIM digitizes all radio audio in-
formation (including non-EPIC radios such

MIC

COM 1 COM 2 COM 3 HF 1 HF 2 SAT PA

AUDIO

NAV 1 NAV 2 NAV 3 ADF 1 ADF 2 ID CABIN FONE

DME 1 DME 2 MKR MUTE XFER CONF

CVR SELCAL ST SPKR ICS HDPH VOX MAINT

SPKR
EMER MIC

NORM EMER BOOM MASK

SPKR : 60

Figure 34-69. Audio Control Panel

FOR TRAINING PURPOSES ONLY 34-91

34-92
MRC 1 MRC 2
NIM 1 NIM 2
ASCB-D

TNIC PROC 1 NIC PROC 3 NIC PROC 5

NIC PROC 2 TNIC PROC 4 NIC PROC 6
CMC SGIO 4
SGIO 1

MAU 3

MAU 1
MAU 2
A B A B A B

A429
A429

A429
SSEC
ANLG DISABLE IRU 1
RS-422 A429
ISI SBDI

FOR TRAINING PURPOSES ONLY

A429
DCM
A429
IRU 2

MAGNETOMETER FLT INSTR BUS FLT INSTR BUS

FLT INSTR BUS

GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL
international
FlightSafety

Figure 34-70. Standby Instruments Block Diagram

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

STANDBY INSTRUMENTS NOTES

Electronic Bearing & Distance
Instrument (EBDI)
The EBDI is a self-contained electronic
standby instrument. The unit provides a dis-
play of heading with reference (magnetic or
true) at the top center of the display. A com-
pass card is provided with increments labeled
every 30° and the cardinal points depicted as
N, E, S, and W respectively. Two bearing
pointers are provided on the compass card.
DME distance is located in the upper left and
right corners of the display. The number one
NAV source is displayed in the lower left cor-
ner of the display, while the number two NAV
source is displayed in the lower right corner.
Heading source is indicated at the lower, cen-
ter portion of the display. When all heading
sources are considered invalid, a red STBY
flag is displayed to the right of the heading
source indication. In an emergency condition,
heading information from all three sources
with the same priority will remain along with
the number one side VOR/ILS data. All ADF,
DME, and number two VOR/ILS information
will be removed from the display.

Integrated Standby Indicator (ISI)

or Standby Flight Display (SFD)
The electronic standby attitude indicator
(ESAI) provides a visual display of attitude
(pitch and roll), and slip/skid information
computed from an internal three-axis inertial
sensor cluster. Air data information for baro-
metrically corrected altitude, air speed, mach
number, and vertical speed are provided by
pitot and static inputs. Built-in interfaces pro-
vide additional navigation information.

The MAG-3000A magnetometer provides

magnetic field information used by the ESAI
to calculate stabilized magnetic heading.

The DCM-3100 detachable configuration mod-

ule retains software and hardware configura-
tion information for specific aircraft.

FOR TRAINING PURPOSES ONLY 34-93

34-94
MRC 1 MRC 2
NIM 1 NIM 2
ASCB-D

TNIC PROC 1 NIC PROC 3 NIC PROC 5

NIC PROC 2 TNIC PROC 4 NIC PROC 6
CMC SGIO 4 SGIO 6
SGIO 1

MAU 3

MAU 1
MAU 2
A B A B A B

ANLG
A429
AUDIO
COCKPIT
AREA AUDIO
MIC. AUDIO ACP 2
CVR

FOR TRAINING PURPOSES ONLY

ACP 1 ACP 3
AUDIO AUDIO

CVR
R ESS DC
POWER
IMPACT RELA Y CVR MED
SWITCH ANLG CWOW
CVR ERASE LOCKED
RELA Y
TEST SWITCH RELA Y
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

SWITCH
international
FlightSafety

Figure 34-71. Cockpit Voice Recorder Block Diagram

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

COCKPIT VOICE RECORDER NOTES

(CVR)
The CVR is an airborne solid-state voice
recorder unit. The CVR continuously accepts
four channels of analog audio information,
converts the analog signals to digital format
and stores the data onto solid-state memory.
The CVR retains the last 30 minutes of each
channel's audio, with the recorder medium
contained in a protective enclosure to guard
against potential damage resulting from an
aircraft accident. The data may be extracted
in digital form from the unit via external con-
nections using a laptop computer. The ex-
tracted digital data is easily converted back to
analog audible form for analysis of events.
In the event of severe damage to the external
connections the data may still be recovered
after removal of the protective enclosures.
The solid-state design requires no moving
p a r t s t h u s r e s u l t i n g i n h i g h r e l i a b i l i t y.
Components that make up the system are:

• CVR Unit
• Cockpit Area Microphone
• Bulk Erase Switch
• Impact Switch

The four audio source channels are the ob-

server, copilot, pilot and remote mounted
cockpit area microphone (MIC). The system
is designed to remove power and stop the
CVR's operation in a safe state upon impact.

A means is provided to the flight crew to bulk

erase the CVR unit's recordings, however, the
design requires the aircraft to first be on the
ground in a weight-on-wheels (WOW) state
with the main cabin door open. The erase
switch is located in the system test panel above
the right side equipment rack just aft of the
flightdeck. It is intended to disallow the bulk
erase function until the aircraft is in a parked,
stationary configuration.

FOR TRAINING PURPOSES ONLY 34-95

34-96
MRC 1 MRC 2
NIM 1 NIM 2
ASCB-D

TNIC PROC 1 NIC PROC 3 NIC PROC 5

NIC PROC 2 TNIC PROC 4 NIC PROC 6
CMC SGIO 4
DGIO 1 CUSTOM IO 2
SGIO 1

MAU 3

MAU 1
MAU 2
CUSTOM IO 1

A B A B A B

ANLG

A717
ANLG
FLIGHT
DATA
RECORDER ACCELEROMETER
ANLG
G350
G450 CMC/FDR
ONLY EVENT FDR

FOR TRAINING PURPOSES ONLY

L ESS DC
SWITCH POWER
RELAY

CWOW
IMPACT
SWITCH
LEFT OR RIGHT G500 GND MAINT
ENGINE FUEL G550 O/RIDE
28 VDC 28 VDC
PRESSURE ONLY
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

SWITCHES
international

Figure 34-72. Flight Data Recorder Block Diagram

FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

FLIGHT DATA RECORDER of WOW to the AIR mode (such as during

takeoff) automatically returns the switch to the
(FDR) AUTO position, enabling FDR recording.
The FDR records and stores digitized data. Manual positioning the switch to the AUTO
The data can be retrieved to assist in recon- position is also possible.
struction of events relevant to an incident.
The FDR continuously records and retains The FDR EVENT switch is located on the
data for a minimum of 25 hours. With electrical cockpit overhead panel (COP). When mo-
power removed, recorded data is retained for mentarily depressed, an event time stamp is
a minimum of two years. The FDR is located placed on the data recorded by the FDR.
in the aft equipment (tail) compartment. It is
international orange in color for high visibil-
ity to aid in location.
NOTES
The flight data recording system receives dig-
itized aircraft operational parameter data from
the MAU. The data is transmitted to a digital
flight data recorder (FDR) and stored in solid-
state memory.

The FDR impact switch, which activates upon

impact, removes power from the FDR.
Removing power prevents pertinent data from
being erased from the FDR. The impact switch
is mounted in the tail compartment near the
FDR. Activation of the impact switch also
causes an annunciator light on the switch hous-
ing to illuminate, remaining illuminated until
the impact switch is reset. Resetting the im-
pact switch is accomplished through the use
of a reset switch, also located on the impact
switch housing.

The underwater locating beacon (ULB) is at-

tached to the FDR. When activated by contact
with water, it transmits a traceable acoustic sig-
nal to aid underwater location of the aircraft
and/or FDR. The ULB receives power from a
self-contained battery.

The FDR maintenance ground override switch

is located on the right electrical equipment
rack (REER) on the system monitor test panel,
and is labeled FDR MAINT GRD OVRD. If
the aircraft is stationary and the weight-on-
wheels (WOW) system is in the GROUND
mode, placing the switch in the OFF position
will inhibit recording by the FDR while air-
craft engines are operating. If the switch is in-
advertently left in the OFF position, transfer

FOR TRAINING PURPOSES ONLY 34-97

 fFLIR WINDOW
COMBINER

34-98
fFLIR ASSY

L MAIN
DC

WIN HEAT CONTROLLER

X AND Y VOLTAGES
DDU
OVERHEAD VIDEO INPUT
UNIT
OHU RS-422

H3 V SYNC
OHU POWER

HV ENABLE

VIDEO DRIVE
fFLIR PROCESSOR
DDU DDU
A429 GOOD POWERED

FOR TRAINING PURPOSES ONLY

HV OVER ASCB DATA

ASCB-D
Other MAUs
AFCS
FMS
VGS/EVS
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

CLEAR SWITCH
MAU 1
international

Figure 34-73. Visual Guidance System Block Diagram

FlightSafety
 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

VISUAL GUIDANCE SYSTEM

(VGS) The pilot is able to maintain excellent situational
The purpose of the visual guidance system awareness and extremely precise aircraft control
(VGS) is to present important aircraft per- that allows operations in restricted visibility con-
formance and control information to the pilot ditions with increased safety. Without reference
within the forward field of view. This is to head-down instruments, the pilot is continual-
achieved by reflecting a picture from a com- ly aware of the aircraft's position, true flightpath,
biner glass that is originally drawn on the face and energy state.
of a CRT. The VGS is designed electrically and
optically so that the data seen by the pilot is The primary components of the VGS are the
collimated and conformal. display driver unit (DDU), the EO-201 over-
head unit (OHU), the CB-200 combiner as-
• Collimated—Focused toward infinity. sembly.
• Conformal—Certain data components The VGS display guidance function is inte-
such as the horizon line and flight path grated into the MAU. Brackets provide align-
vector register correctly, or conform to, ment to the aircraft where either the combiner
the outside, real-world objects that they or OHU can be replaced without realignment.
represent.

Figure 34-74. VGS Combiner

FOR TRAINING PURPOSES ONLY 34-99

34-100
EVS COOL
VALVE

MAU 1
COMBINER EVS
PROCESSOR

MAU 2

FLIR

FOR TRAINING PURPOSES ONLY

WINDOW VGS/EVS
HEAT CONT CLEAR SW.

DC
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

TO MAU 3
WINDOW
international

Figure 34-75. Enhanced Vision System Block Diagram

FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

ENHANCED VISION SYSTEM The EVS is composed of the following ele-

ments:
(EVS)
The enhanced vision system (EVS) increases • Window with integrated heating ele-
the ability of the pilot to see the external en- ments and controls
vironment during periods of low light or re- • Infrared camera (FLIR)
duced visibility by converting infrared
radiation frequencies into visible imagery • Processor
viewed on the visual guidance system (VGS) • HUD combiner lighting controls
head up display (HUD). While normal human
sight is limited to the four hundred to eight • Display controller
hundred (400–800) nanometer frequencies (or • Yoke mounted “EVS clear” switch
4,000–8,000 Angstroms), the forward looking
infrared receiver (FLIR) camera in the EVS de- NOTES
tects frequencies down to the 1,300–4,900
nanometer range. The system camera (FLIR)
is mounted behind a window assembly located
on the aircraft nose beneath the radome. A
channel is positioned in front and above the
window to reduce the flow of rainwater across
the window surface.

The infrared camera field of view is 30 degrees

(30°) horizontally and 20 degrees (20°) ver-
tically. Imagery captured by the camera is
routed through a processor that converts the
infrared picture to a raster format and com-
municates the formatted data to the HUD over-
head unit. The overhead unit synchronizes the
data with the navigational and situational sym-
bology presented on the HUD combiner to
display a congruent image with an extended
visual range.

The composite display imagery of flight guid-

ance cues and infrared heat sources is partic-
ularly effective in low visibility approaches
since the frequency range of the EVS encom-
passes the heat given off by runway and taxi-
way lighting and the higher temperature levels
of the paved surfaces warmed by aircraft
ground operations. The EVS incorporates se-
lective filtration to attenuate or lessen the heat
bloom from runway lights and sequenced
flashers, providing a more refined view of the
airport environment.

FOR TRAINING PURPOSES ONLY 34-101

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-76. SATCOM Block Diagram

34-102 FOR TRAINING PURPOSES ONLY

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

SATCOM NOTES
The Honeywell MCS-7000 is a mobile avion-
ics communications system that supplies con-
tinuous worldwide voice and data
communications services to and from the air-
craft through the INMARSAT satellite net-
work. The services supported by the
MCS-7000 include:

• Cockpit voice and cabin communica-

tions interface for telephony, fax, se-
cure voice and PC modem data.
• Air traffic services (ATS) such as air
traffic control (ATC) and automatic de-
pendent surveillance (ADS).
• Data communications for the evolving
A e r o n a u t i c a l Te l e c o m m u n i c a t i o n s
Network (ATN) and the Future Air
Navigation System (FANS).
• Aeronautical operational control (AOC)
services such as including aircraft com-
munications addressing and reporting
system (ACARS)
• Vo i c e a n d d a t a A e r o n a u t i c a l
Administrative Communications (AAC)

FOR TRAINING PURPOSES ONLY 34-103

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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

Figure 34-77. Satellite Data Unit

Figure 34-78. Spot Beam Coverage

34-104 FOR TRAINING PURPOSES ONLY

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

The MCS-7000 supports a total of seven chan- NOTES

nels and consists of a satellite data unit (SDU)
and a high power amplifier (HPA). A high-gain
antenna is also required but is not a part of the
Honeywell supplied equipment. The MCS-
7000 also supports an ARINC 739 interface to
the MCDUs for SATCOM operations such as
initiating, answering and terminating calls as
well as other maintenance functions. The SDU
can provide storage of 100 phone numbers ar-
ranged into four directories.

FOR TRAINING PURPOSES ONLY 34-105

 ARTU
ARTU MOUNTING TRAY RADIO TEL R T
MAGNASTAR RADIO MAGNASTAR C-2000 10
TEL ANTENNA R MAIN 28 VDC
+28 VDC IN

34-106
+28 VDC +28 VDC
FAN SENSE FAN SENSE
X1 5 RADIO TEL CONT
X2 R MAIN 28 VDC

CDBR-1

LAN LAN TEST

DUPLEXER DIM
+11 VDC + 12 VDC
ANTENNA GND GND OPEN 28 VDC
ANNUN LTS DIM & TEST
TRANSMIT TRANSMIT
RECEIVE RECEIVE CEPT E1

LAN

SDU MASTER PHONE

SATCOM (MCS-7000)
REF 1159AV56028 COMPLETION INITIATE + 28 VDC
CDBR-2
INSTALLATION
+28 VDC

CEPT E1 HOOKSWITCH
LAN
RINGER
AUDIO IN
AUDIO OUT

FOR TRAINING PURPOSES ONLY

MRC 1
NIM
XCVR D AUDIO
XCVR D MIC

SPARE
GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

SPARE
international
FlightSafety

Figure 34-79. MagnaStar Block Diagram

 FlightSafety
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GULFSTREAM G350/G450 MAINTENANCE TRAINING MANUAL

MAGNASTAR C-2000
RADIO/TELEPHONE SYSTEM
The MagnaStar C-2000 radio/telephone sys-
tem is a digital cellular telephone system op-
erating on a network of radio/telephone
(RAD/TEL) stations in the continental United
States, Hawaii, Canada, Mexico and the U.S.
territories of the Bahamas and Santo Domingo.
This network, the Verizon Airfone Ground
Station Network, provides complete North
American service coverage.

The MagnaStar C-2000 system can be used to

send and receive voice calls, data transmissions
via modem and fax transmissions. Up to two
independent calls can be place simultaneously.
Figure 34-80. Air Radio Telecommunications
The system is capable of supporting both ana- Unit (ARTU)
log and digital interface to a multi-channel
SATCOM system.The system provides the
following capabilities: Optional equipment includes analog interface
unit(s) (AIUs) and PBX-switch interfaces.
• Direct Dialing—Calls billed to corporate The ARTU also has the capability to support
account or major credit card a CEPT-El interface for interconnection to
multi-channel digital SATCOM equipment or
• Multiple Phones—Up to nine indepen- other cabin management equipment.
dent handsets
• Fax/ Data modem—provides Fax ma- MagnaStar system also provides the follow-
chine and PC modem interface ing additional features: seat to seat calling,
conference calling, call transfer, data calls,
• TDD (Telecommunication Device for Telephone Device for the Deaf (TDD) calls,
the Deaf) and speed dialing. The system has up to nine
• Direct charge blocking when a/c is char- handsets or stations. These handsets are used
tered. for radiotelephone and SATCOM communi-
cations. Incoming calls will ring the appro-
• Privacy—The transmitted data is digi- priate handset.
tally encoded which ensure privacy from
casual scanning.
The MAGNASTAR C-2000 system is com-
prised of two sections: the digital radio com-
ponents and the installation configurable cabin
distribution components. The C-2000 digital
radio components are an air radio telecom-
munications unit (ARTU), an antenna, a du-
plexer, mounting tray for the ARTU, cabin
data bus repeaters (CDBRs), call alerter switch
(CAS) and telephone handsets.

FOR TRAINING PURPOSES ONLY 34-107