Mar 2017
Page 27
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.
Audio Retention
Following the removal of power from the DAFR, the recorded
information is retained for at least two years for the stipulated
operational and storage environment.
Rotor Tachometer Input
A single-ended rotor speed input is supported by the DAFR.
Input voltage: Range:
1.6V
pk-pk
to 221.4V
pk-pk
.
Input impedance:
≥
10k
Ω
Tail rotor speed 0V return: Rotor_speed _in_lo connected
internally to 0V_Signal.
Pulse frequency range:
10 Hz to 900 Hz.
Sensor source impedance: 100 to 130
Ω
in series with 33
mH or 1200 to 1500
Ω
in series
with 360 mH (Typical).
Accuracy:
Measured to better than ±2%.
Data to Audio Correlation
The DAFR records synchronizing information embedded within
the digitized audio record such that, with appropriate replay
equipment, the relative time between the data and audio
channels can be deduced to within 500 milliseconds.
The source of this synchronizing information is derived from an
internal clock source.
The recorded synchronisation data is embedded within the
audio files downloaded from the recorder via the MTI.
Status Monitoring
Two separate outputs are provided for status monitoring of the
equipment as follows:
FDR FAULT
CVR FAULT
Power-up Tests
A Built-In Test (BIT) routine is executed whenever power is
applied to the system. This routine performs the following:
(i)
Data processor initialization and self check