ENGINE SHUTDOWN (CONT)
(1) INTR LT switch OFF.
(2) SIGHT SEL switch STBY.
For TADS OI aircraft, monitor HOD CRT
as TADS/FLIR switch is placed in OFF.
After approximately 15 seconds, HOD
should flash and loss of SYM BRT control
should be experienced. When symbol
brightness is no longer adjustable, the
system is in independent HOD mode and
power-down can be continued.
Prior to turning TADS off, ensure PNVS is
turned off to allow proper data transfer
into the TADS non-volatile memory.
(3) ACM switch OFF.
(4) TADS switch OFF (verify
(5) ORT SYM BRT switch
Prior to turning IHADSS off, confirm TADS
power down sequence is complete by wait-
ing 30 - 45 seconds after TADS is turned off
and verifying ORT SYM BRT switch is inop-