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will activate the CVR
internal self-test.
COCKPIT VOICE RECORDER MICROPHONE MONITOR
ERASE TEST
STATUS HEADPHONE
COMMUNICATIONS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
06−10−27
REMOTE AREA MICROPHONE
An area microphone is mounted in the flight compartment overhead panel.
GF0610_057
AREA MICROPHONE
IMPACT SWITCH
The impact switch mounted in the aft avionics bay removes electrical power to the CVR when the
airplane experiences an impact.
GF0610_058
AFT AV BAY
IMPACT SWITCH
Audio Control Panel Input
The audio panels provide audio inputs to the CVR for recording flight crew voice communications
and other flight compartment audio signals.
GF0610_059
Audio Control Panel
The various audio signals are summed together in the audio panels to form a single audio input to
the CVR from each audio panel.
COMMUNICATIONS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
06−10−28
CVR SYSTEM SCHEMATIC
DAU 4 (GMT)
AUDIO PANEL 3
(If installed)
AUDIO PANEL 2
AUDIO PANEL 1
IMPACT SWITCH
AREA MIC
GF0610_060
COCKPIT VOICE RECORDER MICROPHONE MONITOR
ERASE TEST
STATUS HEADPHONE
COMMUNICATIONS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
06−10−29
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” push-button for approximately one second to activate the
CVR internal self-test.
GF0610_061
PASSENGER OXYGEN
CLOSED OVERRIDE
NORMAL
FIRST AID
TEST PORT
PASS ON
OFF
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.
NOTE
If a failure occurs during the self test, the green “STATUS” LED will
illuminate continuously and no aural tone will be heard.
"TONE"
GF0610_062
• STATUS − The operation of the green “STATUS” LED is described above under the “TEST”
function.
• ERASE − The “ERASE” push-button 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.
COMMUNICATIONS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
06−10−30
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. A 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.
G−ACCELEROMETER
DAU 4 STATUS
INPUTS
DATA INPUT
FDR
GF0610_063
QUICK ACCESS RECORDER (IF INSTALLED)
The optional Quick Access Recorder (QAR) is an independent flight data recording devise that
records the same data as the FDR. The QAR can retain up to 750 hours of airplane parameters/flight
data. If a QAR failure occurs, the FDR FAIL message will be displayed on EICAS.
COMMUNICATIONS
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
06−10−31
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.
GF0610_064
UNDERWATER
LOCATOR
BEACON
The ULBs operating frequency is 37.5 KHz and will operate for 30 days.
EMERGENCY LOCATOR TRANSMITTER (IF INSTALLED)
The Emergency Locator Transmitter (ELT) is an optional 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
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