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- Radio frequency unit
- High gain antenna.
- Cabin communication system interface via handset
- Airborne data link system
- PC data and fax capability
COMPONENTS AND OPERATION
SATELLITE DATA UNIT (SDU)
Provides interface to all airplane avionics and contains the location of the applicable satellites and rate/frequency translation
for two-voice communication.
RADIO INTERFACE UNIT
The radio interface unit provides three additional simultaneous voice communication channels when operated in conjunction
with the SDU.
HIGH-POWER AMPLIFIER
The high-power amplifier provides rate/frequency power amplification on the L band signals generated by the satellite data
unit or radio frequency unit to a power level required for transmission to the satellite.
SATCOM ANTENNA
The SATCOM system is equipped with one antenna and is located on top of the vertical stabilizer. The SATCOM antenna
is directional and mechanically controlled.
The SATCOM antenna transmits and receives data to the SATCOM LNA/duplexes and the SATCOM antenna control unit
(ACU).
SATCOM ANTENNA CONTROL UNIT
The antenna control unit processes signals from the SATCOM antenna to calculate location. The ACU transmits data to the
SATCOM antenna to control the antenna direction. The ACU gives built-in-test equipment and location data to the SATCOM
transceiver.
DATA LINK (OPTIONAL)
DESCRIPTION
Data link operation is via the VHF, HF, or SATCOM and is controllable from the FMS CDU. The system utilizes the same
data loading unit as the FMS with air-ground-air and air-to-air capabilities. Crew advisory messages are displayed on the
CDU scratch pad.
COMMUNICATIONS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 06-01-13
STATIC WICKS
Static wicks are installed to discharge static electricity, thereby reducing radio interference. They are installed at the following
locations:
- Winglets/wingtips and ailerons
- Elevators, rudder, vertical stabilizer, horizontal stabilizer and tail cone
CFO0601002_005
STATIC WICK
O0601002_006
COMMUNICATIONS
Volume 2 Flight Crew Operating Manual Sep 13/2004
06-01-14 CSP 100-6 REV 1
COCKPIT VOICE RECORDER (CVR)
DESCRIPTION
The solid state cockpit voice recorder (CVR) consists of a flight deck control panel and a recorder unit that is painted bright
orange with reflective stripes. The CVR is mounted in the aft equipment bay.
COMPONENTS AND OPERATION
The CVR receives four channels of audio data from the audio electronics control unit. The recorded information includes
all audio received and transmitted from the following locations:
- Pilot station
- Copilot station
- Area microphone (center of glareshield)
- Observer station
CVR CONTROL PANEL
The CVR control panel is located on the center pedestal and is used to test the CVR system.
The CVR control panel contains:
- A green TEST button and green indicator lamp
- Headset jack
- ERASE button
The CVR starts recording as soon as electrical power is applied to the aircraft. When the aircraft experiences impact deceleration,
electrical power is removed from the recorder to prevent erasure of the stored audio data.
The CVR TEST button, when selected, performs an internal test of the CVR system. A successful test is indicated by illumination
of the green indicator lamp.
When the erase button is pushed, all recorded information will be erased as long as the aircraft is on the ground, the hydraulic
systems are pressurized and the parking brake is set.
CFO0601002_008
COCKPIT VOICE
RECORDER
TEST HEADSET ERASE
HOLD
5 SEC
EV 1
COMMUNICATIONS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 06-01-15
COCKPIT VOICE RECORDER (CVR) (Cont)
AREA MICROPHONE
The area microphone picks up sounds and voices in the flight compartment and is located just above the liquid compass on
the windshield center post.
RECORDER UNIT
The recorder unit is housed inside a crash survivable container. Access to the container is through the aft equipment bay.
The unit records data in a solid state non-volatile memory and stores 120 minutes of recorded information. An underwater
locator device (ULD) is installed on the front of the recorder. The ULD emits a pulsed acoustic signal into the water after
ditching of the aircraft. The ULD sonar beacon is capable of transmitting for up to 30 days after activation.
UNDERWATER ACOUSTIC BEACON
As a further detection aid, the recorder has an underwater locator beacon. the beacon is mounted on the crash survivable
memory unit front bracket to facilitate reading of the batter replacement date as well as for quick removal and replacement
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