T-45A UJPT, E2-C2, ADV & IUT Eng-23
Other T-45A Systems
2.
All detectable failures will be logged in
memory and displayed on the far right side
of PDU
3.
System will return to navigation master
mode when CLR push-button on DEP is
pressed
II.
Airborne data recorder system (ADRS)
Sg 2, fr 1
Lesson Organization
A.
Airborne data recorder system (ADRS) overview
1.4.19.5
1.
Function: provides the combined functions
of a flight incident recorder, engine monitor,
and structural fatigue monitor
2.
Components: airborne data recorder
(ADR), incident record push-button, ADR
BIT panel, and associated aircraft system
sensors
B.
System interface
1.
Electrical: power is provided by 28 VDC
essential services bus and 26 VAC
nonessential bus
2.
The ADR provides N2 speed switching
signals as follows:
a.
N2 < 42% - dump HYD 2 pump
pressure to return to assist engine
starting
b.
N2 > 42% - disconnect external
electrical power
c.
N2 < 70% - disable the steam ingestion
bleed valve
NOTE: Functions are inoperative if
generator, inverter, or nonessential
power lost.
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