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Corrected altitude output = true altitude output increased by height difference
requires positive
altitude correction value
entered when above ADTS
Corrected altitude output = true altitude output decreased by height difference
6.2.40 SET-UP, SPEED, [Pt TEMPERATURE]
The function allows the value of Pt temperature to be entered, this is used in the calculation of TAS.
a.
Enter the Pitot temperature measured by the aircraft's Pitot temperature sensor in the
units shown on the display.
b.
The default units of temperature measurement may be changed using CONFIG, [UNITS],
[TEMPERATURE].
6.2.41 SET-UP, MACH
This function allows the Mach limit to be changed or disabled. The initial Mach limit comes from the
current aircraft limits. To change the limit enter a numeric value or select as follows:
a.
Select [OFF] to disable the Mach limit.
b.
Select [ON] to enable the Mach limit.
c.
Select [DEFAULT] to restore the Mach limit from the aircraft limits in use.
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rack-mounted ADTS 405R
ADTS panel marked reference level
Figure 6-1: Altitude Correction Rack Mounting
Aircraft reference level
ADTS reference level
Figure 6-2: ALTITUDE CORRECTION ON-AIRCRAFT
requires negative
altitude correction value
UUT
entered when below ADTS
UUT reference level
Instruments
STATIC
Air Data
Computer
PITOT
Introduction
ADTS 405 Mk2 Instruction Manual-English | 87
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