Installation Manual

Lynx NGT-9000
Installation Manual
0040-17001-01 (Revision W) Appendix B Page B-2
DESCRIPTION
SECT.
NO. CAT. DESCRIPTION
Overpressure 4.6.3
A1/F1
-15,000 ft.
Temperature Variation 5.3.1 B 5° C/min
Non-controlled temperature, Equipment mounted
internal in aircraft
Humidity 6.3.1 A Standard Humidity Environment
Operational Shocks and
Crash Safety
Operational Shocks 7.2 B
3 shocks of 6g in both directions of the three
orthogonal axes.
Crash Safety 7.3 B
One 20g Impulse shock in both directions
of each orthogonal axis for a total of 6 shocks.
Sustained Aircraft Type 5 (Helicopter and All Fixed-
Wing)
Test Type R (Random Orientation)
Vibration 8
S
Panel Mount: Fixed Wing, Curve M, Sine
Remote Mount: Assuming Fuse Mount: Cat S, Curve L
R
Panel Mount: Robust Fixed Wing, Curves B & B1,
Random
Remote Mount: Curve C/C1
U2 Rotorcraft, Curve F and F1
Explosive Atmosphere 9 X Not Applicable, Not Tested.
Waterproofness 10 X Not Applicable, Not Tested.
Fluids Susceptibility 11 X Not Applicable, Not Tested.
Sand and Dust 12 X Not Applicable, Not Tested.
Fungus Resistance 13 X Not Applicable, Not Tested.
Salt Spray 14 X Not Applicable, Not Tested.
Magnetic Effect 15 Z <0.3m for deflection of D
c
.
Power Input 16 BXX 14V and 28V DC inputs
Voltage Spike 17 A
X
Aircraft Power 28V (no Mod) or Aircraft Power 14V
with HW Mod A (see SB9029000-3):
600 V/2 µs from 50 Ω source impedance
Aircraft Power 14V (without HW Mod A): Not
Applicable, Not Tested.