Loc Track 1 And Bc Track 1; Loc Track 2 And Bc Track 2; True Airspeed (Tas) Gain Programmer - Honeywell SPZ-8000 Pilot's Manual

SPZ--8000 Digital Integrated Flight Control System

LOC TRACK 1 and BC TRACK 1

Localizer track 1 and back course track 1 mean the aircraft is on beam
center and the roll rate limit is decreased from 7.0/second (during the
capture phase) down to 5.5/second. When track occurs, the course error
is eliminated from the control signal, leaving beam deviation and lateral
acceleration from the IRS to maintain the aircraft on beam center. The
track 1 phase occurs when the following conditions are satisfied:
LOC CAP 2 plus 30 seconds
D
Lateral beam rate less than 30 feet/second
D
Localizer beam deviation less than 1/4 dot
D
Aircraft bank angle less than 6_.
D
There is no visual indication in the cockpit that the LOC track 1 or BC track
1 submode has occurred.

LOC TRACK 2 and BC TRACK 2

The track 2 submode occurs only after track 1 has occurred. There is no
visual indication to the pilot that the track 2 mode has been activated.
Radio altitude, distance to the transmitter, and a vertical velocity (indicating
the aircraft is descending) determine the track 2 conditions. When these
conditions reach certain levels, track 2 is tripped to give the flight director
tighter control during the final stages of an approach.
The track 2 phase occurs when the following conditions are all satisfied:
LOC track 1 has been tripped
D
The aircraft is descending at a vertical speed that indicates a runway
D
approach
Either of the following conditions has occurred:
D
— Distance to the transmitter is less than approximately 5 miles and
the radio altimeter is invalid
— Radio altitude is less than 1200 feet with the radio altimeter valid.

True Airspeed (TAS) Gain Programmer

TAS gain programming is used to program heading select/track error,
course select error, PITCH wheel commands, air data commands, and
glideslope deviation to maintain the same aircraft response regardless
of the aircraft's airspeed and altitude. The TAS computation is derived
from airspeed, altitude, and outside air temperature.
System Limits
7-4
A28--1146--055
REV 2