Page 13 of 28 Sym B
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Dwg. 56201-2
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System Wiring
2.5
When ringing out wires in TYCO 1-794617-2 or equivalent connector,
DO NOT insert oversized pins or probe into the main connector.
WARNING
Wire the system in accordance with the Wiring Schematic 70308800-15 Rev. A. Maximum
current in any wire is 0.5 A. All items marked as reference (REF) are to be customer
supplied.
Power for the SCc is supplied through the aircraft power bus. The system is also tied to the
navigation lights, to facilitate day/night dimming. See the Wiring Schematic for details.
Ensure 1.9” minimum bend radius for either CAT5e cable
assembly Do not overcompress either CAT5e cable via
clamping.
NOTE
3704-160-1 should be inserted into Indexer Computer. 3704-150-2 should connect to the
Lift Transducer.
FAA approval of this document includes authorization for
connection of audio output into aircraft audio system. See
Wiring Schematic for details on audio specifications.
NOTE
Lift Transducer Installation
2.6
Connect the Lift Transducer to the Cable Assembly, CAT5E, 3704-150-2.
Mount the Lift Transducer using two screws in the vertical slotted holes on the mounting
plate.
Ground Functional Test
2.7
The Lift Transducer vane should move freely in both directions with no resistance.
With the electrical power OFF the Indexer Computer should not be lit.
Turn the main power ON. The Indexer Computer will perform a Power-on Self-Test,
illuminating all of the LEDs for approximately five seconds. The audio alert will also be active
during the self-test. After the self-test, the audio will cancel and the LEDs will indicate the
current position of the transducer.
The single
red
LED will continue to blink at 1 Hz until the system
has been calibrated in flight.
NOTE
Observe the Indexer Computer for a transition to the low-AoA side of the display, with a
single
green
LED illuminated when the Lift Transducer vane is gently pushed down (AFT).
Gently push the vane up (FORWARD). The Indexer Computer should transition to the high-
AoA side of the display, followed by the flashing of the two
red
LEDs, indicating LAA.
Turn the navigation light switch on and observe Indexer Computer display dims.
The aircraft’s stall warning system is the primary stall warning
.
The
AoA System is non-required equipment and is to be used only as
supplemental information to the pilot
.
CAUTION
