DOC AIRBUS | AMM A320FCOCKPIT VOICE RECORDER (CVR) - DESCRIPTION AND OPERATION
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1. General
The Cockpit Voice Recorder (CVR) is designed to record crew conversations and communications into a Crash Survivable Memory Unit (CSMU) in flight and on the ground, when at least one engine is running or up to five minutes after the last engine stops irrespective of which engine stops first. The system can also operate in manual mode on the ground. The recorder is a four-track system and all tracks are recorded simultaneously.
The CVR provides storage for 30 minutes of consecutive recording for each of the four audio input channels.
When the CSMU is fully recorded, the system progressively erases recordings made in the previous 30 minutes and simultaneously records new information; thus only information recorded in the last 30 minutes of operation is retained. The recorded information can be intentionally erased when the aircraft is on the ground with the parking brake on, locked and electrically powered. Bulk erasure is also possible during manual operation of the system.
The Cockpit Voice Recorder (CVR) is designed to record crew conversations and communications into a memory block unit in flight and on the ground, when at least one engine is running or up to five minutes after the last engine stops irrespective of which engine stops first. The system can also operate in manual mode on the ground. The recorder is a four-track system and all tracks are recorded simultaneously.
The CVR provides storage for 2 hours of consecutive recording for each of the four audio input channels.
When the memory block unit is fully recorded, the system progressively erases recordings made in the previous 2 hours and simultaneously records new information; thus only information recorded in the last 2 hours of operation is retained. The recorded information can be intentionally erased when the aircraft is on the ground with the parking brake on, locked and electrically powered. Bulk erasure is also possible during manual operation of the system.
The Cockpit Voice Recorder (CVR) is designed to record crew conversations, audio communications and datalink communications into a memory unit in flight and on the ground. The CVR operates when at least one engine is running or up to five minutes after the last engine stops irrespective of which engine stops first. It can also operate in manual mode on the ground. The CVR is a four channel system and all channels are recorded simultaneously.
When the memory is full, new data are overwritten on the oldest ones to keep the record of the last 120 minutes. The recorded information can be intentionally erased when the aircraft is on the ground with the parking brake on, locked and electrically powered. Bulk erasure is also possible during manual operation of the system.
It is possible to operate the CVR from the ground and hear the recorded data.
The Cockpit Voice Recorder (CVR) records the crew conversations and communications in a Crash-Survivable Memory Unit (CSMU) in flight and on the ground. The CVR operates when a minimum of one engine is in operation or during a maximum of five minutes after the last engine stops (the engine that stops first is not important). The system can also operate in manual mode on the ground. The CVR is a four-track system and all the tracks are recorded at the same time.
The CVR storage capacity is 2 hours of subsequent record for each of the four audio input channels.
When the CSMU is full, the system gradually erases the records made during the 2 hours before and records new information at the same time. Thus, the CVR keeps only information recorded during the last 2 hours of operation. The recorded information can be intentionally erased when the aircraft is on the ground with the parking brake on, locked and electrically energized. The recorded data can also be fully erased during manual operation of the system.
For more information, refer to the general description and operation of the combined voice and data recording and recording and aircraft locating system TSM 31390003.
Recording of conversations and communications must comply with standards specified by the CAA (Ref. ATA 23-51, Audio Management, para. CAA Recording Function).
** ON A/C NOT FOR ALL The Cockpit Voice Recorder (CVR) is designed to record crew conversations and communications into a Crash Survivable Memory Unit (CSMU) in flight and on the ground, when at least one engine is running or up to five minutes after the last engine stops irrespective of which engine stops first. The system can also operate in manual mode on the ground. The recorder is a four-track system and all tracks are recorded simultaneously.
The CVR provides storage for 30 minutes of consecutive recording for each of the four audio input channels.
When the CSMU is fully recorded, the system progressively erases recordings made in the previous 30 minutes and simultaneously records new information; thus only information recorded in the last 30 minutes of operation is retained. The recorded information can be intentionally erased when the aircraft is on the ground with the parking brake on, locked and electrically powered. Bulk erasure is also possible during manual operation of the system.
The Cockpit Voice Recorder (CVR) is designed to record crew conversations and communications into a memory block unit in flight and on the ground, when at least one engine is running or up to five minutes after the last engine stops irrespective of which engine stops first. The system can also operate in manual mode on the ground. The recorder is a four-track system and all tracks are recorded simultaneously.
The CVR provides storage for 2 hours of consecutive recording for each of the four audio input channels.
When the memory block unit is fully recorded, the system progressively erases recordings made in the previous 2 hours and simultaneously records new information; thus only information recorded in the last 2 hours of operation is retained. The recorded information can be intentionally erased when the aircraft is on the ground with the parking brake on, locked and electrically powered. Bulk erasure is also possible during manual operation of the system.
The Cockpit Voice Recorder (CVR) is designed to record crew conversations, audio communications and datalink communications into a memory unit in flight and on the ground. The CVR operates when at least one engine is running or up to five minutes after the last engine stops irrespective of which engine stops first. It can also operate in manual mode on the ground. The CVR is a four channel system and all channels are recorded simultaneously.
When the memory is full, new data are overwritten on the oldest ones to keep the record of the last 120 minutes. The recorded information can be intentionally erased when the aircraft is on the ground with the parking brake on, locked and electrically powered. Bulk erasure is also possible during manual operation of the system.
It is possible to operate the CVR from the ground and hear the recorded data.
The Cockpit Voice Recorder (CVR) records the crew conversations and communications in a Crash-Survivable Memory Unit (CSMU) in flight and on the ground. The CVR operates when a minimum of one engine is in operation or during a maximum of five minutes after the last engine stops (the engine that stops first is not important). The system can also operate in manual mode on the ground. The CVR is a four-track system and all the tracks are recorded at the same time.
The CVR storage capacity is 2 hours of subsequent record for each of the four audio input channels.
When the CSMU is full, the system gradually erases the records made during the 2 hours before and records new information at the same time. Thus, the CVR keeps only information recorded during the last 2 hours of operation. The recorded information can be intentionally erased when the aircraft is on the ground with the parking brake on, locked and electrically energized. The recorded data can also be fully erased during manual operation of the system.
For more information, refer to the general description and operation of the combined voice and data recording and recording and aircraft locating system TSM 31390003.
Recording of conversations and communications must comply with standards specified by the CAA (Ref. ATA 23-51, Audio Management, para. CAA Recording Function).
2. Component Location
Cockpit Voice Recorder - Component Location ** ON A/C NOT FOR ALL
Cockpit Voice Recorder - Component Location ** ON A/C NOT FOR ALL
Cockpit Voice Recorder (CVR) - Component Location ** ON A/C NOT FOR ALL
CVR - Component Location ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL Cockpit Voice Recorder - Component Location ** ON A/C NOT FOR ALL Cockpit Voice Recorder - Component Location ** ON A/C NOT FOR ALL Cockpit Voice Recorder (CVR) - Component Location ** ON A/C NOT FOR ALL CVR - Component Location ** ON A/C NOT FOR ALL | FIN | FUNCTIONAL DESIGNATION | PANEL | ZONE | ACCESS DOOR | ATA REF |
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| 1RK | CVR | 312AR | 312 | 23-71-35 | |
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| 1RK | CVR | 312 | 23-71-35 | ||
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| 5RK | P/BSW-RCDR/CVR TEST | 21VU | 211 | 23-71-00 | |
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| 11TU | P/BSW-RCDR/GND CTL | 21VU | 211 | 31-33-00 | |
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| 16RK | MIC-CVR | 20VU | 210 | 23-71-13 | |
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| 17RK | MIC-PREAMPLI INTEGRATED, CVR | 20VU | 210 | 23-71-13 | |
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| 18RK | AMPLIFIER-CVR MIC | 212 | 23-71-14 | ||
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| 22RK | JACK-CVR/HEAD SET | 50VU | 210 | 23-71-00 | |
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| 28RK | BOOMSET-CVR | 50VU | 210 | 23-71-00 | |
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| 31TU | P/BSW-RCDR/GND CTL/AUTO | 21VU | 211 | 31-33-00 | |
3. System Description
Cockpit Voice Recorder (CVR) - Block Diagram ** ON A/C NOT FOR ALL
Cockpit Voice Recorder (CVR) - Block Diagram ** ON A/C NOT FOR ALL
Cockpit Voice Recorder (CVR) - Block Diagram ** ON A/C NOT FOR ALL
Cockpit Voice Recorder (CVR) - Block Diagram ** ON A/C NOT FOR ALL
Cockpit Voice Recorder (CVR) - Block Diagram ** ON A/C NOT FOR ALL Cockpit Voice Recorder (CVR) - Block Diagram ** ON A/C NOT FOR ALL Cockpit Voice Recorder (CVR) - Block Diagram ** ON A/C NOT FOR ALL Cockpit Voice Recorder (CVR) - Block Diagram ** ON A/C NOT FOR ALL A. The cockpit voice recorder system consists of:
(1) Remote CVR microphone 16RK for monitoring direct conversations between crew members and aural warnings in the cockpit.
(2) Amplifier 18RK which amplifies the microphone signal.
(3) Cockpit Voice Recorder 1RK which records:
(a) Communications received and transmitted by radio.
(b) Intercom conversations between crew members.
(c) Announcements transmitted over the passenger address system.
(d) Direct conversations between crew members in the cockpit and all aural warnings.
(4) Circuit breaker 23RK supplying the CVR with 28VDC power.
(5) RCDR/CVR ERASE pushbutton switch 3RK which allows complete erasure of the recorder data from the memory block unit.
(6) RCDR/CVR TEST pushbutton switch 5RK which allows recorder test.
(7) CVR/HEAD SET jack 22RK which allows to provide audio return of the CVR TEST and ERASE functions.
(8) Three relays 6RK, 8RK and 10RK which launch the CVR recording mode under specific conditions.
(9) Time-delay relay 10RK which:
- enables the CVR to record for 5 minutes after last engine shutdown, or up to 5 minutes after initially energizing the aircraft electrical network,
- is a back-up in case of a failure of the relay 8RK.
(10) Relay 14RK controlling intentional erasure of the recorder data from the memory block unit and the test signal when the aircraft is on the ground with parking brake applied.
(11) Relays 12TU and 13TU and RCDR/GND CTL pushbutton switch 11TU providing manual control of the CVR when the aircraft is on the ground. On this pushbutton switch, the blue ON legend comes on to indicate that the recorder is in recording mode.
(12) Circuit breaker 26RK supplying the CVR relays (6RK, 8RK , 10RK, 11TU, 12TU and 13TU) with 28VDC power.
(13) Relay 20RK controlling the test signal and ensuring transmission of the TCAS signal (Ref. ATA 34-43).
(14) Remote CVR microphone 16RK for monitoring direct conversations between crew members and aural warnings in the cockpit.
(15) Amplifier 18RK which amplifies the microphone signal.
(16) Cockpit Voice Recorder 1RK which records:
(a) Communications received and transmitted by radio.
(b) Intercom conversations between crew members.
(c) Announcements transmitted over the passenger address system.
(d) Direct conversations between crew members in the cockpit and all aural warnings.
(17) Circuit breaker 2RK supplying the CVR with 115VAC power via the contacts of the relays 6RK and 8RK.
(18) RCDR/CVR ERASE pushbutton switch 3RK which allows complete erasure of the recorder data from the memory block unit.
(19) RCDR/CVR TEST pushbutton switch 5RK which allows recorder test.
(20) CVR/HEAD SET jack 22RK which allows to provide audio return of the CVR TEST and ERASE functions.
(21) Two relays 6RK and 8RK which launch the CVR recording mode under specific conditions.
(22) Time-delay relay 10RK enabling the CVR to record for 5 minutes after last engine shutdown, or up to 5 minutes after initially energizing the aircraft electrical network.
(23) Relay 14RK controlling intentional erasure of the recorder data from the memory block unit and the test signal when the aircraft is on the ground with parking brake applied.
(24) Relays 12TU and 13TU and RCDR/GND CTL pushbutton switch 11TU providing manual control of the CVR when the aircraft is on the ground. On this pushbutton switch, the blue ON legend comes on to indicate that the recorder is in recording mode.
(25) Relay 20RK controlling the test signal and ensuring transmission of the TCAS signal (Ref. ATA 34-43).
(26) Remote CVR microphone 16RK for monitoring direct conversations between crew members and aural warnings in the cockpit.
(27) Amplifier 18RK which amplifies the microphone signal.
(28) Cockpit Voice Recorder 1RK which records:
(a) Communications received and transmitted by radio.
(b) Intercom conversations between crew members.
(c) Announcements transmitted over the passenger address system.
(d) Direct conversations between crew members in the cockpit and all aural warnings.
(e) All necessary datalink communication messages directly from the Air Traffic Control (ATC) applications.
(29) Circuit breaker 23RK supplying the CVR with 28VDC power.
(30) RCDR/CVR ERASE pushbutton switch 3RK which allows complete erasure of the recorder data from the memory block unit.
(31) RCDR/CVR TEST pushbutton switch 5RK which allows recorder test.
(32) CVR/HEAD SET jack 22RK which allows to provide audio return of the CVR TEST and ERASE functions.
(33) Three relays 6RK, 8RK and 10RK which launch the CVR recording mode under specific conditions.
(34) Time-delay relay 10RK which:
- enables the CVR to record for 5 minutes after last engine shutdown, or up to 5 minutes after initially energizing the aircraft electrical network,
- is a back-up in case of a failure of the relay 8RK.
(35) Relay 14RK controlling intentional erasure of the recorder data from the memory block unit and the test signal when the aircraft is on the ground with parking brake applied.
(36) Relays 12TU and 13TU and RCDR/GND CTL pushbutton switch 11TU providing manual control of the CVR when the aircraft is on the ground. On this pushbutton switch, the blue ON legend comes on to indicate that the recorder is in recording mode.
(37) Circuit breaker 26RK supplying the CVR relays (6RK, 8RK , 10RK, 11TU, 12TU and 13TU) with 28VDC power.
(38) Relay 20RK controlling the test signal and ensuring transmission of the TCAS signal (Ref. ATA 34-43).
(39) Remote CVR microphone 16RK for monitoring direct conversations between crew members and aural warnings in the cockpit.
(40) Amplifier 18RK which amplifies the microphone signal.
(41) Cockpit Voice Recorder 1RK which records:
(a) Communications received and transmitted by radio.
(b) Intercom conversations between crew members.
(c) Announcements transmitted over the passenger address system.
(d) Direct conversations between crew members in the cockpit and all aural warnings.
(42) Circuit breaker 2RK supplying the CVR with 115VAC power via the contacts of the relays 6RK and 8RK.
(43) RCDR/CVR ERASE pushbutton switch 3RK which allows complete erasure of the recorder data from the memory block unit.
(44) RCDR/CVR TEST pushbutton switch 5RK which allows recorder test.
(45) CVR/HEAD SET jack 22RK which allows to provide audio return of the CVR TEST and ERASE functions.
(46) Two relays 6RK and 8RK which launch the CVR recording mode under specific conditions.
(47) Time-delay relay 10RK enabling the CVR to record for 5 minutes after last engine shutdown, or up to 5 minutes after initially energizing the aircraft electrical network.
(48) Relay 14RK controlling intentional erasure of the recorder data from the memory block unit and the test signal when the aircraft is on the ground with parking brake applied.
(49) Relays 12TU and 13TU and RCDR/GND CTL pushbutton switch 11TU providing manual control of the CVR when the aircraft is on the ground. On this pushbutton switch, the blue ON legend comes on to indicate that the recorder is in recording mode.
(50) Relay 20RK controlling the test signal and ensuring transmission of the TCAS signal (Ref. ATA 34-43).
(50) Pre-amplified integrated CVR microphone 17RK for monitoring direct conversations between crew members and aural warnings in the cockpit and which amplifies the microphone signal.
(51) Cockpit Voice Recorder 1RK which records:
(a) Communications received and transmitted by radio.
(b) Intercom conversations between crew members.
(c) Announcements transmitted over the passenger address system.
(d) Direct conversations between crew members in the cockpit and all aural warnings.
(e) All necessary datalink communication messages directly from the Air Traffic Control (ATC) applications.
(52) Circuit breaker 23RK supplying the CVR with 28VDC power.
(53) RCDR/CVR ERASE pushbutton switch 3RK which allows complete erasure of the recorder data from the memory block unit.
(54) RCDR/CVR TEST pushbutton switch 5RK which allows recorder test.
(55) CVR/HEAD SET jack 22RK which allows to provide audio return of the CVR TEST and ERASE functions.
(56) Three relays 6RK, 8RK and 10RK which launch the CVR recording mode under specific conditions.
(57) Time-delay relay 10RK which:
- enables the CVR to record for 5 minutes after last engine shutdown, or up to 5 minutes after initially energizing the aircraft electrical network,
- is a back-up in case of a failure of the relay 8RK.
(58) Relay 14RK controlling intentional erasure of the recorder data from the memory block unit and the test signal when the aircraft is on the ground with parking brake applied.
(59) Relays 12TU and 13TU and RCDR/GND CTL pushbutton switch 11TU providing manual control of the CVR when the aircraft is on the ground. On this pushbutton switch, the blue ON legend comes on to indicate that the recorder is in recording mode.
(60) Circuit breaker 26RK supplying the CVR relays (6RK, 8RK , 10RK, 11TU, 12TU and 13TU) with 28VDC power.
(61) Relay 20RK controlling the test signal and ensuring transmission of the TCAS signal (Ref. ATA 34-43).
(62) The pre-amplified integrated CVR-microphone (17RK) which monitors the conversations between the crew members, and the aural warnings in the cockpit. It amplifies the microphone signal.
(63) The CVR (1RK) which records:
(a) Received and transmitted radio communication
(b) Intercom conversations between the crew members
(c) Announcements transmitted with the passenger address system
(d) Conversations between the crew members in the cockpit and all the aural warnings
(e) All necessary datalink communication messages directly from the Air Traffic Control (ATC) applications.
(64) Circuit breaker 23RK which supplies the CVR with 28VDC power.
(65) RCDR/CVR ERASE pushbutton switch 3RK which erases all the recorder data from the memory block unit.
(66) RCDR/CVR TEST pushbutton switch 5RK which is used to do a test of the recorder.
(67) CVR/HEAD SET jack 22RK and CVR boomset 28RK which let the audio return of the CVR TEST and ERASE functions.
(68) Three relays (6RK), (8RK) and (10RK) which start the CVR recording mode in given conditions.
(69) Time-delay relay 10RK which:
- Lets the CVR record data during five minutes after the last engine shutdown, or during a maximum of five minutes after the aircraft electrical network is energized
- Is used as a back-up if a failure of relay 8RK occurs.
(70) Relay 14RK which controls the erasure of the recorder data from the memory block unit and the test signal when the aircraft is on the ground with the parking brake set.
(71) Relays 12TU and 13TU and RCDR/GND CTL pushbutton switch 11TU for manual control of the CVR when the aircraft is on the ground. On this pushbutton switch, the blue ON legend comes on when the recorder is in recording mode.
(72) Circuit breaker 26RK which supplies the CVR relays (6RK, 8RK, 10RK, 11TU, 12TU and 13TU) with 28VDC power.
(73) Relay 20RK which controls the test signal and is used for the transmission of the TCAS signal (Ref. ATA 34-43).
(74) The pre-amplified integrated CVR-microphone (17RK) monitors the conversations between the crew members and the aural warnings in the cockpit. It amplifies the microphone signal.
(75) The CVR (1RK) records:
(a) Received and transmitted radio communications
(b) Intercommunication between the crew members
(c) Announcements that the passenger address system transmits
(d) Conversations between the crew members in the cockpit and all the aural warnings
(e) All necessary datalink-communication messages directly from the Air Traffic Control (ATC) applications.
(76) Circuit breaker 23RK supplies the CVR with 28VDC power.
(77) RCDR/CVR ERASE pushbutton switch 3RK erases all the recorded data from the memory block unit.
(78) RCDR/CVR TEST pushbutton switch 5RK is used to do a test of the recorder.
(79) CVR headset jack 22RK and CVR boomset 28RK let the audio return of the CVR TEST and ERASE functions.
(80) Relays 23TU, 22TU, 24TU, 45TU and 46TU start the CVR recording mode in given conditions.
(81) Time-delay relays 45TU and 46TU:
- Lets the CVR record data during five minutes after the last engine shutdown, or during a maximum of five minutes after the aircraft electrical network is energized
- Is used as a backup if a failure of relay 22TU and/or 24TU occurs.
NOTE: 46TU and 24TU are for ENG1 and 45TU and 22TU are for ENG2.
(82) Relay 14RK controls:
- The erasure of the recorded data from the memory block unit, and
- The test signal when the aircraft is on the ground with the parking brake set.
(83) Relays 25TU and 26TU and RCDR/GND CTL pushbutton switch 31TU are used for the manual control of the CVR when the aircraft is on the ground. On this pushbutton switch, the blue ON legend comes on when the recorder is in recording mode.
(84) Circuit breaker 26RK supplies the CVR relays (22TU, 23TU, 24TU, 45TU, 46TU, 31TU, 25TU and 26TU) with 28VDC power.
(85) Relay 20RK controls the test signal and is used for the transmission of the TCAS signal (Ref. ATA 34-43).
(86) CVR/HEAD SET jack 22RK connected in parallel with the socket on the CVR to facilitate maintenance operations (Ref. para. Component Description - Cockpit Voice Recorder).
(87) CVR/HEAD SET jack 22RK and CVR boomset 28RK connected in parallel with the socket on the CVR to make maintenance easier (Ref. Para. Component Description - Cockpit Voice Recorder).
4. Power Supply
Cockpit Voice Recorder - Schematic ** ON A/C NOT FOR ALL
Cockpit Voice Recorder - Schematic ** ON A/C NOT FOR ALL
CVR - Schematic ** ON A/C NOT FOR ALL
Cockpit Voice Recorder - Schematic ** ON A/C NOT FOR ALL Cockpit Voice Recorder - Schematic ** ON A/C NOT FOR ALL CVR - Schematic ** ON A/C NOT FOR ALL A. Automatic Recording Mode
The CVR is automatically supplied with 115VAC when the aircraft is in one of the configurations given below:
The relays 6RK, 8RK, 10RK are supplied with 28VDC from the busbar 401PP via the circuit breaker 26RK.
The CVR is automatically supplied with 28VDC from busbar 401PP with circuit breaker 23RK when the aircraft is energized.
Relays 22TU, 23TU, 24TU, 45TU and 46TU are supplied with 28VDC from busbar 401PP with circuit breaker 26RK.
The CVR is automatically supplied with 115VAC when the aircraft is in one of the configurations given below:
- In flight with engines running or stopped
- On the ground with at least one engine running
- On the ground during the first five minutes following energization of the aircraft electrical network
- On the ground up to five minutes after second engine shutdown.
- In flight with engines running or stopped
- On the ground with at least one engine running
- On the ground during the first five minutes following energization of the aircraft electrical network
- On the ground up to five minutes after second engine shutdown.
The relays 6RK, 8RK, 10RK are supplied with 28VDC from the busbar 401PP via the circuit breaker 26RK.
The CVR is automatically supplied with 28VDC from busbar 401PP with circuit breaker 23RK when the aircraft is energized.
Relays 22TU, 23TU, 24TU, 45TU and 46TU are supplied with 28VDC from busbar 401PP with circuit breaker 26RK.
(1) Aircraft in flight
The Landing Gear Control and Interface Unit 1 (LGCIU1) 5GA1 sends a ground signal to the relay 6RK.
The relay 6RK is energized.
The CVR is set to the recording mode through the normally-closed contacts of the relay 8RK in parallel with the normally-open contacts of the relay 6RK.
The Landing Gear Control and Interface Unit 1 (LGCIU1) 5GA1 sends a ground signal to the relay 6RK.
The relay 6RK is energized.
The CVR is set to the recording mode through the normally-closed contacts of the relay 8RK in parallel with the normally-open contacts of the relay 6RK.
(2) Aircraft on ground
(a) When one or the two engines are in operation, no ground signal is sent to the relay 10RK. Thus, the relay 10RK is not energized. As the relay 10RK energizes or de-energizes the relay 8RK, the relay 8RK stays de-energized. Therefore, the CVR is set to the recording mode through the normally-closed contact of the relay 8RK.
(b) For the first five minutes after you energize the aircraft electrical network (with both engines stopped), a ground signal is sent to the time-delay relay 10RK.
(c) When the second engine is stopped, a ground signal is sent to the time-delay relay 10RK.
NOTE: In the conditions specified in Para. (2) (b) and (c) above, when the relay 10RK is energized, it starts its timing function. During this timing function, the contact of the relay 10RK stays open, the relay 8RK stays de-energized, and the CVR is set to the recording mode through the normally-closed contact of the relay 8RK.
After 5 minutes, the relay 10RK stays energized, the timing function stops and its contact closes. This energizes the relay 8RK, its contact opens and the CVR stops the recording.
After 5 minutes, the relay 10RK stays energized, the timing function stops and its contact closes. This energizes the relay 8RK, its contact opens and the CVR stops the recording.
NOTE: In the conditions specified in Para. (2) above, the relay 6RK is de-energized (aircraft on the ground).
(3) Aircraft in flight
The Landing Gear Control and Interface Unit 1 (LGCIU1) 5GA1 sends a ground signal to the relay 6RK.
The relay 6RK is energized.
The CVR is set to the recording mode through the normally-closed contacts of the relay 8RK in parallel with the normally-open contacts of the relay 6RK.
The Landing Gear Control and Interface Unit 1 (LGCIU1) 5GA1 sends a ground signal to the relay 6RK.
The relay 6RK is energized.
The CVR is set to the recording mode through the normally-closed contacts of the relay 8RK in parallel with the normally-open contacts of the relay 6RK.
(4) Aircraft on ground
(a) When one or the two engines are in operation, no ground signal is sent to the relay 10RK. Thus, the relay 10RK is not energized. As the relay 10RK energizes or de-energizes the relay 8RK, the relay 8RK stays de-energized. Therefore, the CVR is set to the recording mode through the normally-closed contact of the relay 8RK.
(b) For the first five minutes after you energize the aircraft electrical network (with both engines stopped), a ground signal is sent to the time-delay relay 10RK.
(c) When the second engine is stopped, a ground signal is sent to the time-delay relay 10RK.
NOTE: In the conditions specified in Para. (2) (b) and (c) above, when the relay 10RK is energized, it starts its timing function. During this timing function, the contact of the relay 10RK stays open, the relay 8RK stays de-energized, and the CVR is set to the recording mode through the normally-closed contact of the relay 8RK.
After 5 minutes, the relay 10RK stays energized, the timing function stops and its contact closes. This energizes the relay 8RK, its contact opens and the CVR stops the recording.
After 5 minutes, the relay 10RK stays energized, the timing function stops and its contact closes. This energizes the relay 8RK, its contact opens and the CVR stops the recording.
NOTE: In the conditions specified in Para. (2) above, the relay 6RK is de-energized (aircraft on the ground).
(5) Aircraft in flight
The Landing Gear Control and Interface Unit 1 (LGCIU1) 5GA1 sends a ground signal to the relay 6RK.
The relay 6RK is energized.
The CVR is set to the recording mode through the normally-closed contacts of the relays 8RK and 10RK in parallel with the normally-open contact of the relay 6RK.
The Landing Gear Control and Interface Unit 1 (LGCIU1) 5GA1 sends a ground signal to the relay 6RK.
The relay 6RK is energized.
The CVR is set to the recording mode through the normally-closed contacts of the relays 8RK and 10RK in parallel with the normally-open contact of the relay 6RK.
(6) Aircraft on ground
(a) When one or the two engines are in operation, no ground signal is sent to the relay 10RK. Thus, the relay 10RK is not energized. As the relay 10RK energizes or de-energizes the relay 8RK through its normally-open contact, the relay 8RK stays de-energized. Therefore, the CVR is set to the recording mode through the normally-closed contacts of the relays 8RK and 10RK.
(b) For the first five minutes after you energize the aircraft electrical network (with both engines stopped), a ground signal is sent to the time-delay relay 10RK.
(c) When the second engine is stopped, a ground signal is sent to the time-delay relay 10RK.
NOTE: In the conditions specified in Para. (2) (b) and (c) above, when the relay 10RK is energized, it starts its timing function. During this timing function, the normally-open contact of the relay 10RK stays open, the relay 8RK stays de-energized, and the CVR is set to the recording mode through the normally-closed contacts of the relays 8RK and 10RK.
After 5 minutes, the relay 10RK stays energized, the timing function stops and its normally-open contact closes. This energizes the relay 8RK, the normally-closed contact of the relay 10RK opens and the CVR stops the recording.
After 5 minutes, the relay 10RK stays energized, the timing function stops and its normally-open contact closes. This energizes the relay 8RK, the normally-closed contact of the relay 10RK opens and the CVR stops the recording.
NOTE: In the conditions specified in Para. (2) above, the relay 6RK is de-energized (aircraft on the ground).
(7) Aircraft in flight
LGCIU1 (5GA1) sends a ground signal to relay 23TU.
Relay 23TU is energized.
The CVR is set to the recording mode with the usually-closed contacts of relays 22TU, 24TU, 45TU and 46TU in parallel with the usually-open contact of relay 23TU.
LGCIU1 (5GA1) sends a ground signal to relay 23TU.
Relay 23TU is energized.
The CVR is set to the recording mode with the usually-closed contacts of relays 22TU, 24TU, 45TU and 46TU in parallel with the usually-open contact of relay 23TU.
(8) Aircraft on ground
NOTE: 46TU and 24TU are for ENG1 and 45TU and 22TU are for ENG2.
(a) When one or the two engines is(are) in operation, no ground signal is sent to relay 45TU and/or 46TU. Thus, relay 45TU and/or 46TU is not energized. Because relay 45TU and/or 46TU energizes or de-energizes relay 22TU and /or 24TU with the usually-open contact, relay 22TU and/or 24TU stays de-energized. Thus, the CVR is set to the recording mode with the usually-closed contacts of relays 22TU and/or 24TU and 45TU and/or 46TU.
(b) For the first five minutes after you energize the aircraft electrical network (with the two engines stopped), a ground signal is sent to time-delay relay 45TU and/or 46TU.
(c) When the second engine is stopped, a ground signal is sent to time-delay relay 45TU and/or 46TU.
NOTE: In the conditions specified in Para. (2) (b) and (c), when relay 45TU and/or 46TU is energized, it starts its timing function. During this timing function, the usually-open contact of relay 45TU and/or 46TU stays open, relay 22TU and/or 24TU stays de-energized, and the CVR is set to the recording mode with the usually-closed contacts of relays 22TU, 24TU, 45TU and 46TU.
After five minutes, relay 45TU and/or 46TU stays energized, the timing function stops and its usually-open contact closes. This energizes relay 22TU and/or 24TU and the usually-closed contact of relay 45TU and/or 46TU opens and the CVR stops the recording.
After five minutes, relay 45TU and/or 46TU stays energized, the timing function stops and its usually-open contact closes. This energizes relay 22TU and/or 24TU and the usually-closed contact of relay 45TU and/or 46TU opens and the CVR stops the recording.
NOTE: In the conditions specified in Para. (2), relay 23TU is de-energized (aircraft on the ground).
B. Manual Recording Mode
When you supply power manually to the CVR, with the aircraft on the ground and the two engines stopped, you can:
When you supply power manually to the CVR, with the aircraft on the ground and the two engines stopped, you can:
When you supply power manually to the CVR, with the aircraft on the ground and the two engines stopped, you can:
When you supply power manually to the CVR, with the aircraft on the ground and the two engines stopped, you can:
- Do a functional test of the CVR,
- Record the beginning of the check list before you start the first engine,
- Erase the crash-survivable memory unit data if necessary.
When you supply power manually to the CVR, with the aircraft on the ground and the two engines stopped, you can:
- Do a functional test of the CVR,
- Record the beginning of the check list before you start the first engine,
- Erase the crash-survivable memory unit data if necessary.
When you supply power manually to the CVR, with the aircraft on the ground and the two engines stopped, you can:
- Do a functional test of the CVR,
- Record the beginning of the check list before you start the first engine,
(1) When you push RCDR/GND CTL pushbutton switch 11TU, the ON legend comes on.
When the two engines are stopped, a ground signal is sent to relay 12TU.
When you push RCDR/GND CTL pushbutton switch 11TU, relay 12TU is supplied with 28VDC through the contacts of relay 13TU. Relay 12TU is energized. A ground signal is sent to the blue ON legend which comes on.
Because a ground signal is also sent to relay 6RK, the CVR is set to the recording mode.
When you release RCDR/GND CTL pushbutton switch 11TU, relay 13TU is supplied with 28VDC through relay 12TU.
When the two engines are stopped, a ground signal is sent to relay 12TU.
When you push RCDR/GND CTL pushbutton switch 11TU, relay 12TU is supplied with 28VDC through the contacts of relay 13TU. Relay 12TU is energized. A ground signal is sent to the blue ON legend which comes on.
Because a ground signal is also sent to relay 6RK, the CVR is set to the recording mode.
When you release RCDR/GND CTL pushbutton switch 11TU, relay 13TU is supplied with 28VDC through relay 12TU.
(2) When you push RCDR/GND CTL pushbutton switch, the ON legend goes off.
When you push RCDR/GND CTL pushbutton switch 11TU again, relay 13TU is de-energized.
Relay 12TU stays energized through the contacts of relay 13TU. A ground signal continues to be sent to the blue ON legend which stays on.
Because a ground signal is also sent to relay 6RK, the CVR is set to the recording mode.
When you release RCDR/GND CTL pushbutton switch 11TU, the contact opens and de-energizes relay 12TU. The blue ON legend goes off, relay 6RK is de-energized and the CVR stops the recording.
When you push RCDR/GND CTL pushbutton switch 11TU again, relay 13TU is de-energized.
Relay 12TU stays energized through the contacts of relay 13TU. A ground signal continues to be sent to the blue ON legend which stays on.
Because a ground signal is also sent to relay 6RK, the CVR is set to the recording mode.
When you release RCDR/GND CTL pushbutton switch 11TU, the contact opens and de-energizes relay 12TU. The blue ON legend goes off, relay 6RK is de-energized and the CVR stops the recording.
NOTE: If you start one engine, the ground signal to relay 12TU is removed and relay 12TU is de-energized. The blue ON legend goes off and relay 6RK is de-energized. The CVR stays in the recording mode through the normally-closed contact of relay 8RK.
(3) When you push RCDR/GND CTL pushbutton switch 31TU, the ON legend comes on.
When the two engines are stopped, a ground signal is sent to relay 25TU.
When you push RCDR/GND CTL pushbutton switch 31TU, relay 25TU is supplied with 28VDC with the contacts of relay 26TU. Relay 25TU is energized. A ground signal is sent to the blue ON legend which comes on.
Because a ground signal is also sent to relay 23TU, the CVR is set to the recording mode.
When you release RCDR/GND CTL pushbutton switch 31TU, relay 26TU is supplied with 28VDC with relay 25TU.
When the two engines are stopped, a ground signal is sent to relay 25TU.
When you push RCDR/GND CTL pushbutton switch 31TU, relay 25TU is supplied with 28VDC with the contacts of relay 26TU. Relay 25TU is energized. A ground signal is sent to the blue ON legend which comes on.
Because a ground signal is also sent to relay 23TU, the CVR is set to the recording mode.
When you release RCDR/GND CTL pushbutton switch 31TU, relay 26TU is supplied with 28VDC with relay 25TU.
(4) When you push RCDR/GND CTL pushbutton switch, the ON legend goes off.
When you push RCDR/GND CTL pushbutton switch 31TU again, relay 26TU is de-energized.
Relay 25TU stays energized with the contacts of relay 26TU. A ground signal continues to be sent to the blue ON legend which stays on.
Because a ground signal is also sent to relay 23TU, the CVR is set to the recording mode.
When you release RCDR/GND CTL pushbutton switch 31TU, the contact opens and de-energizes relay 25TU. The blue ON legend goes off, relay 23TU is de-energized and the CVR stops the recording.
When you push RCDR/GND CTL pushbutton switch 31TU again, relay 26TU is de-energized.
Relay 25TU stays energized with the contacts of relay 26TU. A ground signal continues to be sent to the blue ON legend which stays on.
Because a ground signal is also sent to relay 23TU, the CVR is set to the recording mode.
When you release RCDR/GND CTL pushbutton switch 31TU, the contact opens and de-energizes relay 25TU. The blue ON legend goes off, relay 23TU is de-energized and the CVR stops the recording.
NOTE: If you start one engine, the ground signal to relay 25TU is removed and relay 25TU is de-energized. The blue ON legend goes off and relay 23TU is de-energized. The CVR stays in the recording mode with the usually-closed contact of relay 22TU or 24TU.
5. Interface
Ref. Para. System Description
** ON A/C NOT FOR ALL Ref. Para. System Description
6. Component Location
A. Cockpit Voice Recorder Microphone Amplifier 18RK
The CVR Microphone amplifier is attached behind the overhead panel.
Two electrical connectors are provided at the back for connection with the CVR and the remote microphone.
Inside is the microphone pre-amplifier which is supplied with 18VDC from the Cockpit Voice Recorder.
The cockpit voice recorder microphone amplifier is a Solid State Cockpit Voice Recorder (SSCVR) microphone amplifier.
The SSCVR Microphone amplifier is attached behind the overhead panel.
Two electrical connectors are provided at the back for connection with the CVR and the remote microphone.
Inside is the microphone pre-amplifier which is supplied with 18VDC from the Cockpit Voice Recorder.
The CVR Microphone amplifier is attached behind the overhead panel.
Two electrical connectors are provided at the back for connection with the CVR and the remote microphone.
Inside is the microphone pre-amplifier which is supplied with 18VDC from the Cockpit Voice Recorder.
The cockpit voice recorder microphone amplifier is a Solid State Cockpit Voice Recorder (SSCVR) microphone amplifier.
The SSCVR Microphone amplifier is attached behind the overhead panel.
Two electrical connectors are provided at the back for connection with the CVR and the remote microphone.
Inside is the microphone pre-amplifier which is supplied with 18VDC from the Cockpit Voice Recorder.
B. Cockpit Voice Recorder Microphone 16RK or 17RK
The remote microphone is installed at the bottom of the overhead panel.
It is a condenser type microphone.
The pre-amplified integrated CVR-microphone is a digital microphone with a pre-amplified function.
The remote microphone is installed at the bottom of the overhead panel.
It is a condenser type microphone.
The cockpit voice recorder microphone is a Solid State Cockpit Voice Recorder (SSCVR) microphone.
The remote microphone is installed at the bottom of the overhead panel.
It is a condenser type microphone.
The remote microphone is installed at the bottom of the overhead panel.
It is a condenser type microphone.
The pre-amplified integrated CVR-microphone is a digital microphone with a pre-amplified function.
The remote microphone is installed at the bottom of the overhead panel.
It is a condenser type microphone.
The cockpit voice recorder microphone is a Solid State Cockpit Voice Recorder (SSCVR) microphone.
The remote microphone is installed at the bottom of the overhead panel.
It is a condenser type microphone.
C. Cockpit Voice Recorder (CVR) 1RK
CVR - Component Description ** ON A/C NOT FOR ALL
SSCVR - Component Description ** ON A/C NOT FOR ALL
The CVR is a Solid State Cockpit Voice Recorder (SSCVR).
The SSCVR is located in the aft section of the aircraft.
It is attached to a shockmount by means of two locking tabs.
The CVR is a Solid State Cockpit Voice Recorder (SSCVR).
The SSCVR is located in the aft section of the aircraft.
It is attached to a shockmount by means of two locking tabs.
CVR - Component Description ** ON A/C NOT FOR ALL SSCVR - Component Description ** ON A/C NOT FOR ALL The SSCVR is located in the aft section of the aircraft.
It is attached to a shockmount by means of two locking tabs.
The CVR is a Solid State Cockpit Voice Recorder (SSCVR).
The SSCVR is located in the aft section of the aircraft.
It is attached to a shockmount by means of two locking tabs.
(a) An Underwater Locator Beacon (ULB) is mounted on a bracket attached to the recorder. The ULB is a battery-operated device which radiates a pulsed acoustic signal into the surrounding water upon activation of its water-sensitive switch. It consists of a self-contained battery, an electronic module and a transducer. The battery is shock-mounted and separated from the electronic module by a bulkhead built into the case; it is accessible by removal of the end cover which is sealed with an O-ring. Located on the opposite end of the ULB is a teflon-insulated water-sensitive switch.
(b) A BITE indicator provides an indication of the health of the SSCVR. If the SSCVR detects a fault which requires removal of the unit from the aircraft installation, the BITE indicator will activate and will remain activated until repair is accomplished. The BITE indicator remains inactive in all other cases.
(a) An Underwater Locator Beacon (ULB) is mounted on a bracket attached to the recorder. The ULB is a battery-operated device which radiates a pulsed acoustic signal into the surrounding water upon activation of its water-sensitive switch. It consists of a self-contained battery, an electronic module and a transducer. The battery is shock-mounted and separated from the electronic module by a bulkhead built into the case ; it is accessible by removal of the end cover which is sealed with an O-ring. Located on the opposite end of the ULB is a teflon-insulated water-sensitive switch.
(b) An Automatic Test Equipment connector provides an interface for a portable device.
(3) Inside the recorder:
CVR - Component Description ** ON A/C NOT FOR ALL
SSCVR - Component Description ** ON A/C NOT FOR ALL
CVR - Component Description ** ON A/C NOT FOR ALL SSCVR - Component Description ** ON A/C NOT FOR ALL (a) The SSCVR consists of three Shop Replaceable Units (SRUs) (not including the basic system chassis):
- Controller Board A1 (interface and Control)
The interface and Control board is a single circuit card which controls all states and modes of the system performing the record, erase and test functions of the system. The interface and control board provides all functional interfaces to external systems. - Crash-survivable memory unit
The crash-survivable memory unit is a solid state, nonvolatile mass storage device enclosed in a protective case. The crash survivable memory unit provides storage for all input data. - Power supply converts either 115VAC 400Hz or 28VDC aircraft power into secondary power for Shop Replaceable Units (SRUs) and provides power on reset and power failure monitoring.
(4) Inside the recorder:
Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL
Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL
Cockpit Voice Recorder (CVR) - Operation ** ON A/C NOT FOR ALL
CVR - Operation ** ON A/C NOT FOR ALL
SSCVR - Component Description ** ON A/C NOT FOR ALL
SSCVR - Component Description ** ON A/C NOT FOR ALL
Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL Cockpit Voice Recorder (CVR) - Operation ** ON A/C NOT FOR ALL CVR - Operation ** ON A/C NOT FOR ALL SSCVR - Component Description ** ON A/C NOT FOR ALL SSCVR - Component Description ** ON A/C NOT FOR ALL (a) The CVR consists of three Shop Replaceable Units (SRUs) (not including the basic system chassis):
- Controller Board A1 (interface and Control)
The interface and Control board is a single circuit card which controls all states and modes of the system performing the record, erase and test functions of the system. The interface and control board provides all functional interfaces to external systems. - Crash-survivable memory unit
The crash-survivable memory unit is a solid state, nonvolatile mass storage device enclosed in a protective case. The crash survivable memory unit provides storage for all input data. - Power supply converts 28VDC aircraft power into secondary power for Shop Replaceable Units (SRUs) and provides power on reset and power failure monitoring.
(5) Inside the recorder: The SSCVR consists of three Shop Replaceable Units (SRUs) not including the basic system chassis: an interface and Control board, a crash survivable memory unit, and a power supply. The interface and control board is a single circuit card which controls all states and modes of the system performing the record, erase, and test functions of the system. The interface and control board provides all functional interfaces to external systems. The crash survivable memory unit is a solid state, non-volatile, mass storage device enclosed in a protective case. The crash survivable memory unit provides storage for all input data. The power supply converts either 115VAC 400Hz or +28VDC aircraft power to the secondary power for the SRUs and provides power on reset, power failure monitoring, and significant power interrupt capability.
7. Operation
A. Recording
Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL
Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL
Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL
Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL
Cockpit Voice Recorder (CVR) - Operation ** ON A/C NOT FOR ALL
CVR - Operation ** ON A/C NOT FOR ALL
Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL Cockpit Voice Recorder - Operation ** ON A/C NOT FOR ALL Cockpit Voice Recorder (CVR) - Operation ** ON A/C NOT FOR ALL CVR - Operation ** ON A/C NOT FOR ALL B. Recording Channels
The recording system includes four recording channels which record four audio signals at the same time as follows:
Channels 1, 2 and 3 have a narrow band which makes possible the recording of signals from the CAPT, F/O and third occupant with AMU 1RN.
Channel 4 has a wide band which makes possible the recording of the ambient noises that the area microphone collects. These noises are sent to the input transformer of channel 4 with a pre-amplifier.
Each channel sends data to a dedicated solid-state memory.
The recordings are made on the crash protected memory which gives a 30-minute maximum record-interval of continuous operation.
The primary function of the SSCVR is to record audio digital communication-data and timing data in the crash-survivable memory unit.
The SSCVR also includes the erase and test functions that the operator starts. The operator uses pushbutton switches in the cockpit to activate discrete control signals. To control the operation, the operator also does a power-up initialization and a power-down monitoring. To download the stored data and to do return-to-service and acceptance tests of the unit, the SSCVR also operates in downloading and test modes.
Channels 1, 2 and 3 have a narrow band which makes possible the recording of signals from the CAPT, F/O and third occupant with AMU 1RN.
Channel 4 has a wide band which makes possible the recording of the ambient noises that the area microphone collects. These noises are sent to the input transformer of channel 4 with a pre-amplifier.
The three narrow band channels are recorded separately during the first 30 minutes and are mixed together from 30 minutes to 120 minutes.
The recordings are made on the crash protected memory which gives a 120-minute maximum record-interval of continuous operation.
The primary function of the SSCVR is to record audio digital communication-data and timing data in the crash-survivable memory unit.
The SSCVR also includes the erase and test functions that the operator starts. The operator uses pushbutton switches in the cockpit to activate discrete control signals. To control the operation, the operator also does a power-up initialization and a power-down monitoring. To download the stored data and to do return-to-service and acceptance tests of the unit, the SSCVR also operates in downloading and test modes.
Channels 1, 2 and 3 make possible the recording of signals from the CAPT, F/O and third occupant with AMU 1RN.
Channel 4 makes possible the recording of the ambient noises that the area microphone collects. These noises are sent to the input transformer of channel 4 with a pre-amplifier.
Each channel sends data to a dedicated solid-state memory.
These audio signals are supplied through the rear connector. Then, they are digitally changed, compressed and stored in a memory.
These four signals are recorded at high audio quality for 120 minutes.
All the four channels are sent to the flash memory of the crash-survivable memory unit for storage.
The primary function of the SSCVR is to record audio digital communication-data and timing data in the crash-survivable memory unit.
The recording system includes four recording channels which record four audio signals at the same time as follows:
Channels 1, 2 and 3 have a narrow band which makes possible the recording of signals from the CAPT, F/O and third occupant with AMU 1RN.
Channel 4 has a wide band which makes possible the recording of the ambient noises that the area microphone collects. These noises are sent to the input transformer of channel 4 with a pre-amplifier.
Each channel sends data to a dedicated solid-state memory.
The recordings are made on the crash protected memory which gives a 30-minute maximum record-interval of continuous operation.
The primary function of the SSCVR is to record audio digital communication-data and timing data in the crash-survivable memory unit.
The SSCVR also includes the erase and test functions that the operator starts. The operator uses pushbutton switches in the cockpit to activate discrete control signals. To control the operation, the operator also does a power-up initialization and a power-down monitoring. To download the stored data and to do return-to-service and acceptance tests of the unit, the SSCVR also operates in downloading and test modes.
NOTE: The SSCVR is synchronized with the second aircraft recorder (SSFDR) with an audio signal which agrees with the GMT that the FDIU sent to the audio system and that the SSCVR received on the third occupant channel.
The recording system includes four recording channels which record four audio signals at the same time as follows:Channels 1, 2 and 3 have a narrow band which makes possible the recording of signals from the CAPT, F/O and third occupant with AMU 1RN.
Channel 4 has a wide band which makes possible the recording of the ambient noises that the area microphone collects. These noises are sent to the input transformer of channel 4 with a pre-amplifier.
The three narrow band channels are recorded separately during the first 30 minutes and are mixed together from 30 minutes to 120 minutes.
The recordings are made on the crash protected memory which gives a 120-minute maximum record-interval of continuous operation.
The primary function of the SSCVR is to record audio digital communication-data and timing data in the crash-survivable memory unit.
The SSCVR also includes the erase and test functions that the operator starts. The operator uses pushbutton switches in the cockpit to activate discrete control signals. To control the operation, the operator also does a power-up initialization and a power-down monitoring. To download the stored data and to do return-to-service and acceptance tests of the unit, the SSCVR also operates in downloading and test modes.
NOTE: The SSCVR is synchronized with the second aircraft recorder (SSFDR) with an audio signal which agrees with the GMT that the FDIU sent to the audio system and that the SSCVR received on the third occupant channel.
The recording system includes four recording channels which record the four audio signals at the same time as follows:Channels 1, 2 and 3 make possible the recording of signals from the CAPT, F/O and third occupant with AMU 1RN.
Channel 4 makes possible the recording of the ambient noises that the area microphone collects. These noises are sent to the input transformer of channel 4 with a pre-amplifier.
Each channel sends data to a dedicated solid-state memory.
These audio signals are supplied through the rear connector. Then, they are digitally changed, compressed and stored in a memory.
These four signals are recorded at high audio quality for 120 minutes.
All the four channels are sent to the flash memory of the crash-survivable memory unit for storage.
The primary function of the SSCVR is to record audio digital communication-data and timing data in the crash-survivable memory unit.
NOTE: The SSCVR is synchronized with the second aircraft recorder (SSFDR) with an audio signal which agrees with the GMT that the FDIU sent to the audio system and that the SSCVR received on the third occupant channel.
C. Erasure
(1) Manual erasure
The bulk erase sequence is initiated from the RCDR/CVR ERASE pushbutton switch 3RK. To prevent accidental erasure, this pushbutton switch must be pushed for at least one-half second and the landing gear must be down with the aircraft weight on and parking brake ON.
The bulk erase sequence is initiated from the RCDR/CVR ERASE pushbutton switch 3RK. To prevent accidental erasure, this pushbutton switch must be pushed for at least one-half second and the landing gear must be down with the aircraft weight on and parking brake ON.
NOTE: The Cockpit Voice Recorder is energized for 5 minutes after the second engine stops.
A +30VDC signal (erase charge signal), generated by the bulk erase timing assembly, is applied to the coil of relay RY1 through:
A +30VDC signal (erase charge signal), generated by the bulk erase timing assembly, is applied to the coil of relay RY1 through:
- The normally-open (NO) contacts of SYS 2 L/G position relay 12GB
- The normally-open (NO) contacts of relay 14RK, this relay being energized when parking brake is ON
- The normally-open (NO) contacts of the RCDR/CVR ERASE pushbutton switch.
NOTE: The timing circuit in the Cockpit Voice Recorder activates the relay RY1 for 5 seconds (minimum). This ensures that the complete crash-survivable memory unit is erased.
(2) Automatic erasure
The erase head is permanently activated by a signal generated by the bias oscillator when the recorder is supplied with 115VAC at 400 Hz. The erase head erases the previously recorded information on all 4 channels simultaneously before a new recording is made.
The erase head is permanently activated by a signal generated by the bias oscillator when the recorder is supplied with 115VAC at 400 Hz. The erase head erases the previously recorded information on all 4 channels simultaneously before a new recording is made.
(3) Manual erasure
The bulk erase sequence is initiated from the RCDR/CVR ERASE pushbutton switch 3RK. To prevent accidental erasure, this pushbutton switch must be pushed for at least two seconds and the landing gear must be down with the aircraft weight on and parking brake ON.
The bulk erase sequence is initiated from the RCDR/CVR ERASE pushbutton switch 3RK. To prevent accidental erasure, this pushbutton switch must be pushed for at least two seconds and the landing gear must be down with the aircraft weight on and parking brake ON.
NOTE: The Cockpit Voice Recorder is in recording mode for 5 minutes after the second engine stops.
A +30VDC signal (erase charge signal), generated by the bulk erase timing assembly, is applied to the coil of relay RY1 through:
A +30VDC signal (erase charge signal), generated by the bulk erase timing assembly, is applied to the coil of relay RY1 through:
- The normally-open (NO) contacts of SYS 2 L/G position relay 12GB,
- The normally-open (NO) contacts of relay 14RK, this relay being energized when parking brake is ON,
- The normally-open (NO) contacts of the RCDR/CVR ERASE pushbutton switch.
NOTE: The timing circuit in the Cockpit Voice Recorder activates the relay RY1 for 5 seconds (minimum). This ensures that the complete tape is erased.
(4) Automatic erasure
The erase head is permanently activated by a signal generated by the bias oscillator when the recorder is in recording mode. The erase head erases the previously recorded information on all 4 channels simultaneously before a new recording is made.
The erase head is permanently activated by a signal generated by the bias oscillator when the recorder is in recording mode. The erase head erases the previously recorded information on all 4 channels simultaneously before a new recording is made.
(5) Manual erasure
The bulk erase sequence is initiated from the RCDR/CVR ERASE pushbutton switch 3RK. To prevent accidental erasure, this pushbutton switch must be pushed for at least two seconds and the landing gear must be down with the aircraft weight on and parking brake ON.
The bulk erase sequence is initiated from the RCDR/CVR ERASE pushbutton switch 3RK. To prevent accidental erasure, this pushbutton switch must be pushed for at least two seconds and the landing gear must be down with the aircraft weight on and parking brake ON.
NOTE: The Cockpit Voice Recorder is energized for 5 minutes after the second engine stops.
A +30VDC signal (erase charge signal), generated by the bulk erase timing assembly, is applied to the coil of relay RY1 through:
A +30VDC signal (erase charge signal), generated by the bulk erase timing assembly, is applied to the coil of relay RY1 through:
- The normally-open (NO) contacts of SYS 2 L/G position relay 12GB
- The normally-open (NO) contacts of relay 14RK, this relay being energized when parking brake is ON
- The normally-open (NO) contacts of the RCDR/CVR ERASE pushbutton switch.
NOTE: The timing circuit in the Cockpit Voice Recorder activates the relay RY1 for 5 seconds (minimum). This ensures that the complete CSMU is erased.
(6) Automatic erasure
The erase head is permanently activated by a signal generated by the bias oscillator when the recorder is supplied with 115VAC at 400 Hz. The erase head erases the previously recorded information on all 4 channels simultaneously before a new recording is made.
The erase head is permanently activated by a signal generated by the bias oscillator when the recorder is supplied with 115VAC at 400 Hz. The erase head erases the previously recorded information on all 4 channels simultaneously before a new recording is made.
8. Test
The Push-To-Test function is activated using a discrete input of the SSCVR (activated using the RCDR/CVR TEST pushbutton switch 5RK located on the overhead panel). The discrete must be activated for a minimum of one-half second to activate this function. Once activated, this function performs an extensive set of functional tests to determine the integrity of the system. A successful self-test results in the status discrete output being activated once.This results in one activation of the status LED (whichever is present) on the SSCVR. In addition to the visual indication, an aural indication is provided through the audio monitor output received at the CVR/HEAD SET JACK (on the maintenance panel 50VU) or at the two loud speakers an 800 Hz tone is sent to indicate successful self-test. There is one pulse.
The Push-To-Test function is activated using a discrete input of the SSCVR (activated using the RCDR/CVR TEST pushbutton switch 5RK located on the overhead panel). The discrete must be activated for a minimum of five seconds to activate this function. Once activated, this function performs an extensive set of functional tests to determine the integrity of the system. A successful self-test results in the status discrete output being activated once.This results in one activation of the status LED (whichever is present) on the SSCVR. In addition to the visual indication, an aural indication is provided through the audio monitor output received at the CVR/HEAD SET JACK (on the maintenance panel 50VU) or at the two loud speakers an 600 Hz tone is sent to indicate successful self-test.
The Push-To-Test function is activated using a discrete input of the SSCVR (activated using the RCDR/CVR TEST pushbutton switch 5RK located on the overhead panel). Once activated, this function performs an extensive set of functional tests to determine the integrity of the system. A successful self-test results in the status discrete output being activated once.This results in one activation of the status LED (whichever is present) on the SSCVR. In addition to the visual indication, a short tone is provided through the audio monitor output to :
This tone only shows that the test is in progress.
When you speak into one of the hand microphones and you can hear your voice in the headset connected to CVR/HEADSET jack 22RK or connected to CVR boomset 28RK, it shows that the SSCVR is serviceable.
The Push-To-Test function is activated using a discrete input of the SSCVR (activated using the RCDR/CVR TEST pushbutton switch 5RK located on the overhead panel). The discrete must be activated for approximately two seconds to activate this function. Once activated, a tone is provided through the audio monitor output to the CVR/HEADSET jack 22RK (on the maintenance panel 50VU).
This tone indicates only that the test is in progress.
When you speak into one of the hand microphones and you can hear your voice in the headset connected to jack 22 RK, this indicates that the SSCVR is operational.
The tone is amplified to the two loudspeakers (to the HEADSET jack on the CVR and to the CVR/HEAD SET jack on the maintenance panel 50VU) for aural indication.
A short tone is sent to the headset jack and to the loud speakers for aural indication.
A 800Hz tone is sent to the headset jack and to the loud speakers for aural indication.
The Push-To-Test function is activated using a discrete input of the SSCVR (activated using the RCDR/CVR TEST pushbutton switch 5RK located on the overhead panel). The discrete must be activated for a minimum of one-half second to activate this function. Once activated, this function performs an extensive set of functional tests to determine the integrity of the system. A successful self-test results in the status discrete output being activated once.This results in one activation of the status LED (whichever is present) on the SSCVR. In addition to the visual indication, an aural indication is provided through the audio monitor output received at the CVR/HEAD SET JACK (on the maintenance panel 50VU) or at the two loud speakers an 800 Hz tone is sent to indicate successful self-test. There is one pulse.
The Push-To-Test function is activated using a discrete input of the SSCVR (activated using the RCDR/CVR TEST pushbutton switch 5RK located on the overhead panel). The discrete must be activated for a minimum of five seconds to activate this function. Once activated, this function performs an extensive set of functional tests to determine the integrity of the system. A successful self-test results in the status discrete output being activated once.This results in one activation of the status LED (whichever is present) on the SSCVR. In addition to the visual indication, an aural indication is provided through the audio monitor output received at the CVR/HEAD SET JACK (on the maintenance panel 50VU) or at the two loud speakers an 600 Hz tone is sent to indicate successful self-test.
The Push-To-Test function is activated using a discrete input of the SSCVR (activated using the RCDR/CVR TEST pushbutton switch 5RK located on the overhead panel). Once activated, this function performs an extensive set of functional tests to determine the integrity of the system. A successful self-test results in the status discrete output being activated once.This results in one activation of the status LED (whichever is present) on the SSCVR. In addition to the visual indication, a short tone is provided through the audio monitor output to :
- The two loudspeakers
- The CVR/HEAD SET JACK (on the maintenance panel 50VU) if the headset is connected.
This tone only shows that the test is in progress.
When you speak into one of the hand microphones and you can hear your voice in the headset connected to CVR/HEADSET jack 22RK or connected to CVR boomset 28RK, it shows that the SSCVR is serviceable.
The Push-To-Test function is activated using a discrete input of the SSCVR (activated using the RCDR/CVR TEST pushbutton switch 5RK located on the overhead panel). The discrete must be activated for approximately two seconds to activate this function. Once activated, a tone is provided through the audio monitor output to the CVR/HEADSET jack 22RK (on the maintenance panel 50VU).
This tone indicates only that the test is in progress.
When you speak into one of the hand microphones and you can hear your voice in the headset connected to jack 22 RK, this indicates that the SSCVR is operational.
The tone is amplified to the two loudspeakers (to the HEADSET jack on the CVR and to the CVR/HEAD SET jack on the maintenance panel 50VU) for aural indication.
A short tone is sent to the headset jack and to the loud speakers for aural indication.
A 800Hz tone is sent to the headset jack and to the loud speakers for aural indication.