Mar 2017 Page 43
© 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.
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
5 OPERATING INSTRUCTIONS
NOTE:
The procedure described here refers to installations
with a separate Penny & Giles Aerospace Ltd Cockpit
Control Unit type D51616-XXXX.
5.1 GENERAL
Operation of the DAFR is automatic when power is applied via
the connector.
CAUTION:
IT IS NECESSARY TO REMOVE THE DATA ACQUISITION
FLIGHT RECORDER TYPE D51615-202-XXX FOR
MAINTENANCE. POWER MUST BE SWITCHED OFF AT
LEAST FIVE SECONDS BEFORE THE UNIT IS
DISCONNECTED FROM THE AIRCRAFT.
5.2 CONTROLS AND INDICATORS
The Cockpit Control Unit Type D51616-XXXX provides two
push-buttons for ‘TEST’ and ‘ERASE, a biased toggle switch
for ‘FDR RCRD’ (ARINC 757 FDR INHIBIT function), two
cockpit mounted indicators ‘CVR FAIL’ and ‘FDR FAIL’, and a
Headphone Jack.
5.2.1 TEST Pushbutton
Momentary operation of the TEST pushbutton initiates the
Built-In-Test (BIT) function. Both the CVR FAIL and FDR FAIL
indicators should illuminate for eight seconds and then
extinguish.
NOTE:
The BIT function is automatic on application of power
to the DAFR. It is therefore not mandatory to have a
cockpit mounted TEST Pushbutton.
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