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ON
SPKR
OFF
MIC MASK
HI
SENS
LO
SENS
VHF 3
BOTH
I
D
V
O
I
C
E
TRANSMIT EMER
VHF 1
NAV 1
SPEAKER HEADPHONE
NAV 2 ADF DME
ST MKR MUTE H'MIC
INT
VHF 2 HF 1 HF 2 PA
1 21 2
SPKR
ON
SPKR
OFF
MIC MASK
HI
SENS
LO
SENS
VHF 3
BOTH
I
D
V
O
I
C
E
For Training Purposes Only
Sept 04
5-31
P I LOT T R A I N I N G GU I D E
COMMUNICATIONS
MICROPHONE MONITOR CONTROL PANEL TEST
The cockpit voice recorder microphone monitor panel TEST, STATUS and ERASE
functions are as follows:
• TEST – Push and hold the TEST pushbutton for approximately 1/2 second to
activate the CVR internal self-test
A successful test will result in the green STATUS LED illuminating for one second,
and a two second aural tone will be heard using the headphone, as long as the
headphone is plugged into the CVR port shown on the diagram above.
NOTE
If a failure occurs during the self-test, the green STATUS LED
will illuminate continuously, and no aural tone will be heard.
COCKPIT VOICE RECORDER MICROPHONE MONITOR
ERASE
STATUS
TEST
HEADPHONE
PUSH TO CLOSE
OPEN
PUSH
OPEN
PUSH
PPR
ADV
TEST
ALRT
RSTY
OFF
FAULT
LOW
PPR
THERAPEUTIC
OXYGEN
ON
PASSENGER OXYGEN NORMAL
CLOSED OVERRIDE TEST PORT
PASS. ON
OXYGEN
MASK
PRESS
TO
TEST
AND
RESET
EROS
EMERGENCY
100%
PUSH
OXYGEN SUPPLY LOWER
DISCONNECT
ON
OFF
GX_05_043
ERASE
STATUS
GX_05_044
“TONE”
P I LOT T R A I N I N G GU I D E
COMMUNICATIONS
5-32 For Training Purposes Only
Sept 04
• STATUS – The operation of the green STATUS LED is described above under the
TEST function
• ERASE – The ERASE pushbutton is used to initiate a memory erase sequence
within the CVR. The CVR logic ensures that the ERASE function is only enabled
when the airplane is on the ground (WOW), and the parking brake set
FLIGHT DATA RECORDER
The Flight Data Recorder (FDR) is a crash survivable data recorder capable of
retaining up to 25 hours of airplane parameters/flight data. The FDR system consists
of:
• Solid state flight data recorder
• High-G accelerometer
The High-G accelerometer is mounted in the airplane landing gear bay and provides
the normal acceleration data for the FDR system.
The DAU 4 receives airplane parameters/flight data from various systems, and normal
acceleration input from a dedicated accelerometer. The FDR receives its systems
information from DAU 4 and sends status information back to the DAU 4.
An FDR self-test is performed on airplane power-up and if a failure is detected (at any
time including self-test), an advisory message will be displayed on EICAS.
GX_05_045
INPUTS DAU 4
DATA INPUT
STATUS
G-ACCELEROMETER
FDR
For Training Purposes Only
Sept 04
5-33
P I LOT T R A I N I N G GU I D E
COMMUNICATIONS
UNDERWATER LOCATOR BEACON
An Underwater Locator Beacon (ULB) is attached to the CVR as part of the handle to
help locate it in the event of a crash.
The ULB’s operating frequency is 37.5 kHz, and it will operate for 30 days.
EMERGENCY LOCATOR TRANSMITTER
The Emergency Locator Transmitter (ELT) is an operational system and consists of:
• ELT switch
• Emergency locator transmitter
• ELT antenna
A flight compartment switch, located on the overhead panel, provides ON and ARM
modes of operation. The switch can be used to manually activate the ELT for test
purposes or emergency situations.
LIGHT SENSOR – ELT PANEL
The ELT transmits signals on 121.5, 243.0, and 406.025 MHz. The 406.025 MHz
signal is transmitted for satellite relay. Upon activation, the 121.5, 243.0 signals
operate continuously until the self-contained battery pack power is exhausted
(typically last at least 72 hours) or the unit is reset. The output signal of the 406 MHz
transmitter is transmitted for 24 hours (once every 47 seconds) then automatically
shuts off. It transmits tail number, owner and emergency phone number. An optional
nav interface box can be installed, which will then also transmit the last GPS latitude
and longitude to the satellite.
GX_05_046
Underwater
Locator Beacon
ELT
ARM/
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