Mar 2017 Page 96
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.
SECTION
REQUIREMENT CCU & CAM
23 Lightning Direct Effects X
24 Icing X
25 ESD A
Table 12 : Cockpit Equipment Environmental Test Levels
NOTES:
1. The CCU and CAM derive power from the DAFR and
these tests are not applicable
2. The microphone pre-amplifier Signal to Noise ratio
may be reduced to 35 dB under this test condition.
The CAM induced signal level shall not exceed a
level equivalent to an applied sound pressure
level of 50 dB above 20Pa.
3. The microphone pre-amplifier Signal to Noise ratio
may be reduced to 35 dB under this test condition.
For the CAM, the test level for radiated
susceptibility shall be 2V/m from 30 MHz to 1.215
GHz. For the CAM, the test level for conducted
susceptibility shall be 3 mA (2V/m) from 500 kHz
to 400 MHz, and from 500 kHz to 10 kHz shall fall
at the rate of 6 dB per octave (20 dB per decade).
2 STORAGE
The Cockpit Control Unit is delivered in a standard Penny &
Giles trade container, unless otherwise negotiated with the
Customer, and should remain in this container until required
for use. With the units packaged as received, the storage life
will be 36 months over the temperature range of -25C to
+40C with a relative humidity not exceeding 75%. The
packaging should be retained for future use.
3 UNPACKING
CAUTION:
CARE MUST BE TAKEN WHEN UNPACKING AND
HANDLING THE CONTROL UNIT TYPE D51616-XXXX TO
ENSURE THAT THE UNIT NOT SUFFER UNDUE SHOCK
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