Test Panel - BMS F-16C/D 4.34 Flight Manual

T.O. BMS1F-16CM-1

1.2.1.1 TEST panel

The TEST panel is used to perform tests on different systems during Ramp start. In
BMS all switches and push buttons are implemented, except the FLCS TEST switch in
the MAINT (Maintenance) position.
The FIRE & OHEAT DETECT button checks continuity for both engine fire and
overheat detection systems. The overheat detection happens 100°C before the engine
fire detection system. The overheat triggers the OVERHEAT caution light and the
engine fire triggers the ENG FIRE eyebrow light. Those lights and the MASTER
CAUTION light remain on as long as the button is held depressed.
The second pushbutton on the panel is MAL & IND LTS. It tests the illumination of all warning,
caution, indicator lights, the warning horn and all voice messages in sequence.
The OXY QTY is a momentary switch and tests the OBOGS (On Board Oxygen Generating System).
When depressed the OXY LOW eyebrow light should illuminate for 10 seconds if no faults are
present and remain on if a fault is detected. Please note in newer blocks this switch should be
labelled OBOGS BIT.
The PROBEHEAT switch is a three-position switch: PROBE HEAT, OFF and TEST.
The pitot, fuselage air data, AOA and the total temperature probe heaters are on anytime the aircraft
is airborne regardless of the TEST panel switch position.
The PROBEHEAT position allows the probes to be heated on the ground. OFF de-energizes all
systems on the ground. TEST (on the ground and in-flight) performs a functional test of the
PROBEHEAT monitoring system. The PROBEHEAT caution light flashes for a successful test.
Failure of the PROBEHEAT caution light to illuminate or flash indicates a failure of the probe heat
monitoring system.
The EPU/GEN test switch is spring loaded to the OFF position and provides a means to test the EPU
generator and EPU PMG output to FLCS on the ground without using hydrazine. Hydrazine is highly
toxic for ground personnel and special procedures have to be followed when the EPU has run on
hydrazine.
The quad indicator labelled FLCS PWR is the indicator of the 4 redundant digital systems (ABDC) of
the FLCS (Flight Control System). In BMS they are considered as one and always light up together.
The FLCS PWR TEST switch is a momentary switch to TEST. With the MAIN PWR switch in BATT it
closes the FLCS relay and allows verification of power output to the FLCC (Flight Control Computer)
with the aircraft battery as the power source.
BMS Key Callbacks for the test panel:
SimOverHeat
SimOBOGSBit
SimMalIndLights
SimMalIndLightsOFF
SimProbeHeatMoveDown
SimProbeHeatMoveUp
SimProbeHeatOn
SimProbeHeatOff
SimProbeHeatTest
SimEpuGenTest
SimFlcsPowerTest
BMS 4.34 Dash 1
© Red Dog 2012-2019
BMS 4.34 Change 2.00
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