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
__________________
(Ref. Fig. 001)
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS| ATA | | | | DOOR | REF.
-------------------------------------------------------------------------------1RK CVR 312 312AR 23-71-35 3RK P/BSW-RCDR/CVR ERASE 21VU 211 5RK P/BSW-RCDR/CVR TEST 21VU 211
16RK MIC-CVR 20VU 210 23-71-13 18RK AMPLIFIER-CVR MIC 212 23-71-14 11TU P/BSW-RCDR/GND CTL 21VU 211 22RK JACK-CVR/HEAD SET 50VU 210
3. System Description
__________________
(Ref. Fig. 002)
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)
Solid State 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 2RK supplying the CVR with 115VAC power via the contacts of the relays 6RK and 8RK.
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Cockpit Voice Recorder - Component Location Figure 001
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Cockpit Voice Recorder - Block Diagram Figure 002
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(5)
RCDR/CVR ERASE pushbutton switch 3RK which provides complete erasure of the recorder data from the CSMU.
(6)
RCDR/CVR TEST pushbutton switch 5RK which provides recorder test.
(7)
Two relays 6RK and 8RK which automatically energize and de-energize the CVR under specific conditions.
(8)
Time-delay relay 10RK enabling the CVR to operate for 5 minutes after last engine shut-down, or up to 5 minutes after initially energizing the aircraft electrical network when the recorder is automatically switched on.
(9)
Relay 14RK controlling intentional erasure of the recorder data from CSMU and the test signal when the aircraft is on the ground with parking brake applied.
(10)
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 blues ON legend comes on to indicate that the recorder is operating.
(11)
Relay 20RK controlling the test signal and ensuring transmission of the TCAS signal (TCAS see 3443).
(12)
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).
4. Power Supply____________ (Ref. Fig. 003)
A. Automatic Power Supply 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.
(1) Aircraft in flight The LGCIU1 5GA1 provides a ground signal to the relay 6RK. The relay 6RK is supplied directly with 28VDC from the bus bar 801PP via the circuit breaker 4RK. The CVR is supplied with 115VAC via the normally-open contacts of the relay 6RK from the bus bar 801XP through the circuit breaker 2RK.
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Cockpit Voice Recorder - Schematic Figure 003
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The normally-closed contacts of the relay 8RK provide a parallel path with the normally-open contacts of the relay 6RK for the supply of 115VAC to the CVR.
(2) Aircraft on ground
(a)
With one or both engines running, no ground signal is fed to the relay 10RK. Since the relay 10RK controls the energized or de-energized state of relay 8RK, the relay 8RK remains de-energized. The 115VAC is connected from the bus bar 801XP via the circuit breaker 2RK through the normally-closed contacts of the relay 8RK to the CVR.
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