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STAB
NU
NL RUDDER
LWD RWD
NR
TRIMS
7.2
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4
5750
115
81
93.4
5750
115
81
EPR
N1
ITT
AIL
1.65 1.65
CRZ
AP1 FLC
2250
HUD
Computer
FLIGHT INSTRUMENTS
Rev 5, Jul 21, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
11−10−55
HEAD-UP DISPLAY SYSTEM (HUD) (CONT'D)
HeadUp
Display Computer
The HUD Computer is mounted in the avionics bay and interfaces with the airplanes avionic and
electrical systems. 28 VDC is supplied to the HUD Computer from the DC BUS 2 via the EMS
CDU and is controlled by the HUD BRT/DIM knob located on the glareshield. The HUD Computer
computes the position, value and brightness of symbols.
The computer is composed of two independent computation channels (COMmand) and (MONitor)
The COM channel performs the following:
· Input/Output (I/O) Processing − performs acquisition and validation of avionics data and
sensor selection consistent with PFD and data comparison.
· Symbology Computation − performs automatic Mode management (based on airplane flight
configuration), confirms the presence or absence of each symbol and position of the
displayed symbols.
· Display Generation − generates deflection and blanking signals.
The MON channel performs the following:
· Input/Output (I/O) Processing − performs acquisition and validation of avionics data and
sensor selection consistent with PFD and data comparison.
· Display Monitoring − monitors symbols position, numerical readout value and presence,
verification of deflection signals of 3 referenced points and compares the current value with
a theoretical value.
· COU Monitoring − monitors the operational position based on infrared
emission by the OPU
and the reflection on a mirror located on the combiner.
· Built in Test − verifies the functionality and integrity of the system.
The acquisition module monitors the following data:
· Attitude (Pitch and Roll angle)
· Magnetic heading
· Computed airspeed
· Baro altitude
· Radio Altitude
· Localizer deviation (via IAC)
· Gideslope deviation (via IAC)
The COM and MON channels use the following sensors:
Channel Sensors
COM IRS 1 ADC 1 IAC 1 RAD 1 DAU 4A SPC 1
MON IRS 2 ADC 2 IAC 2 RAD 2 DAU 4B SPC 2
BOTH ADC 3 IAC 3 EGPWS TCAS
The IAC busses provide the following:
· General airplane configuration − Pilot and Copilot sensor selection, navigation/FMS data
and airplane parameters (speed, system status, AP/FD/AT modes).
· Radio information and data integrity, such as VOR/ILS, DME and ADF.
FLIGHT INSTRUMENTS
Flight Crew Operating Manual Rev 5, Jul 21, 2005
CSP 700−5000−6
Volume 2
11−10−56
HEAD-UP DISPLAY SYSTEM (HUD) (CONT'D)
Optical Projector Unit
The Optical Projector Unit draws an image on the screen of a cathode ray tube (CRT) and this
image is projected through a relay lens to the separate Combiner Unit.
The Optical Projector Unit is fitted with:
· Optical lens assembly
· Display circuits
· Internal monitoring devices
· Failure detection devices
· Combiner Unit position sensor.
Optical Projector Unit
Combiner Unit
NOTE
The Optical Projector Unit is hidden behind the headliner.
GF1110_060
FLIGHT INSTRUMENTS
Rev 5, Jul 21, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
11−10−57
HEAD-UP DISPLAY SYSTEM (HUD) (CONT'D)
Combiner Unit
The Combiner Unit superimposes the image drawn by the Optical Projector Unit and is fitted with:
· An ambient light detector (photovoltaic cell).
· A mirror for position monitoring (enables the position detecting device to verify if the
Combiner Unit is in the correct position).
· A stowage and breakaway system.
The Combiner can be selected in three different positions:
· Stowed position, when the HUD is not being used.
· Operational position, to allow symbology display.
· A crash position, in the event of an emergency.
GF1110_061 Ambient Light
Sensor Handle
Stowed Position
Lock Marks
Holographic Glass
Extended Position
Operational Position
Lock Marks
Crash Reset
Button
Holographic Glass
Crash Position
HUD Brightness Control Knob
　
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