Mar 2017
Page 28
DATA ACQUISITION FLIGHT RECORDER Type D51615-202-XXX or D51615-
202-XXX-090 with CCU Type D51616-XXXX and CAM Type D51623-XXXX
Installation and Operating Manual with Illustrated Parts
List
Commercial in Confidence
PIM434-I
© Penny & Giles Aerospace Ltd. No part of this work may be reproduced or distributed by any means
without prior permission in writing from the copyright owner.
(ii)
Audio processor initialization and self check
(iii)
Program Memory validation for both processors
(iv)
Non-volatile housekeeping validation
(v)
Audio encoding circuitry initialization
(vi)
Interface integrity checks (if option configured).
Any failure of the above tests causes a corresponding FAULT
status for the audio or data (or both) recording system which
is latched until power is removed or a subsequent test is
passed satisfactorily.
Continuous Tests (Data)
During normal operation BIT routines are executed to
continuously monitor the following aspects of the data
recording system:
(i)
Data processor program sequence
(ii)
Protected memory ‘read-after-write’
(iii)
Valid recording of flight data
(iv)
Ability to meet statutory minimum storage duration
(v)
Interface integrity checks (if option configured).
The presence of a failure of any of the above tests causes an
FDR FAULT status to be asserted. Should the fault clear, the
FDR FAULT indication is removed.
Continuous Tests (Audio)
During normal operation BIT routines are executed to
continuously monitor the following aspects of the audio
recording system:
(i)
Audio processor program sequence
(ii)
Protected memory ‘read-after-write’
(iii)
Audio channel operation
(iv) Audio
recording continuity
(v)
Ability to meet statutory minimum storage duration
(vi)
Interface integrity checks (if option configured)