GH-3100
Installation & Operation Manual
TP-559
Operation
Page 5-27
Revision K
March 30, 2017
5.3.2.1 Fast Erect
Selecting Fast Erect through the main menu causes a rapid alignment of the vertical axis shown on the
indicator to the current vertical axis of the aircraft. During FAST ERECT, aircraft must remain in straight
and level, non-accelerated flight.
5.3.2.2 Fast Align
Selecting Fast Align through the main menu causes a rapid erection of the vertical axis shown on the
display to the current vertical axis of the aircraft and a 90-second sensor alignment.
During the Fast Align mode the "ATT FAIL", the "Aligning" message and a counter that indicates the
number of seconds remaining in the alignment process is shown.
The counter is reset to 90 seconds if during the Fast Align the unit detects roll motion greater than
±
5.0
degrees or pitch motion greater than
±
3.0 degrees. An "ALIGNMENT FAIL" is shown on the display if
after six minutes the unit has not reached normal mode.
NOTE
Use the Fast Erect function first to remove attitude errors. If errors are
not reduced use the Fast Align function as described above.
5.3.3 Slip / Skid Indicator
The Slip / Skid data is derived from the internal sensors of the unit. The scaling of the Slip / Skid
Indicator is such that rotating the unit by 8
°
±
1
°
about the roll axis shall result in the slip / skid indicator
deflecting to its maximum deflection of 2.25
±
0.25 indicator lengths. The operational limit of the slip/skid
indicator is 8
°
±
1
°
. The direction of the deflection of the Slip / Skid Indicator shall be right for clockwise
rotation of the nit and left for counter-clockwise rotation.
Rotating the unit by 1° about the roll axis results in perceptible displacement of the Slip / Skid Indicator
from its zero position. The speed of the Slip / Skid Indicator is such that with the unit at rest and rotated
by 12° about the roll axis, a sudden rotation to 12° in the other direction causes the Slip / Skid Indicator to
reach the opposite limit within 0.5 to 2.0 seconds after crossing zero.
5.3.4 Air Data Display
The pressure altitude, baro corrected altitude, mach, computed airspeed and optional vertical speed is
supplied by the unit. The static source error correction (SSEC) curve and maximum allowable airspeed
curve is supplied to the unit by the DCM-3100, except as described in the NOTE below.
5.3.4.1 Altitude
Altitude display data is calculated from the unit baro correction setting, SSEC curve(s) and the pressure
transducers.
5.3.4.2 IAS
The IAS data is calculated from data supplied from the pressure transducers.
Configuration Option: IAS can be modified as follows K1 + K2 (IAS). [K1 and K2 are configuration
entries in the DCM].
