COMPONENT MAINTENANCE MANUAL
AVIATION PRODUCTS
Model FA5000
Rev. 02 Page 42
July 21/17
Description and Operation
23–70
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30
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the restrictions on the cover page of this document.
Failure of the recorder to
store Information In the
storage medium
Failure of the recorder to
store Information In the
storage medium
Insufficient audio or UTC
time record duration
Insufficient datalink record
duration
CVR Inhibited (pin 10 acti-
vated)
CVR Inhibited (pin 10 acti-
vated)
(3) Data Link (ATC)
Interface
The FA5000CVR, interface with the Data Link Systems from other aircraft pro-
grams (ATSU on SA/LR or even CMU).
The FA5000CVR is designed to support V3 Williamsburg Protocol high and V1
Williamsburg hardware provision.
The “data link recording” information status is taken into account by the A429
CVR output through the label 350 bit 16. (0 = ok and 1=failure), as per ARINC
757/A.
The CVR receives all data link messages on pins 33/34 (DATALINK IN 429) as
per ARINC 757/A characteristics.
D. Push
−
to
−
Test (PTT) Functionality
The Push
−
to
−
Test functionality (already implemented on existing aircraft and stan-
dardized in ARINC 757/A specification) is used to provide the flight crew with the
ability to quickly confirm good serviceability of the CVR before flight as required by
the applicable regulation.
Upon test activation, the CVR tests the front end audio inputs (each of the four au-
dios inputs channels) and initiates Built
−
In
−
Test functions of the CVR.
Upon initiation of the Push
−
To
−
Test (PTT) function, the CVR sends status indication
on dedicated outputs, particularly on CVR fault discrete output pin 23 (not used) and
on label 350 (CVR STATUS WORD bit 11 on pins 50/51).
CVR Test activation (PTT switch) is allowed at any time during the flight so that the
crew can re
−
initiate the test after a fault is detected in the hope of recovering the
recorder (test is specified to act as a reset of the recorder).
E. Bulk Erase
As per ARINC 757/A, the CVR provides a Bulk erase function. In order to ensure re-
liable operation, the function is inhibited to prevent inadvertent or untimely erasure
while the aircraft is capable of moving under its own power. In addition to the means
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