# BendixKing KLN 89B - Pilots Guide User Manual

## Page 138

4.5.5.

THE CALCULATOR 5 (CAL 5) PAGE

The CAL 5 page is used to determine density altitude.

To calculate the density altitude:

1.

Turn on the cursor (

B

).

2.

The pressure altitude (Prs) displayed will be either the last
pressure altitude from the CAL 4
page. If you desire to change it,
enter the current pressure alti-
tude to the nearest hundred feet
or ten meters by using the right
inner knob (figure 4-87).

3.

Use the right outer knob to move the cursor to the first Temp:

field, and then use the right inner and outer knobs to enter the

outside air temperature (degrees
Celsius) (figure 4-88). The first
digit of the temperature is either
“0” if the temperature is above
zero or “-” if the temperature is
below zero. For maximum
accuracy, the static air tempera-
ture should be entered. This is the temperature of air without the
effect of heating due to the aircraft’s movement through the air.
For the airspeeds of most piston aircraft, the difference between
static air temperature and the observed air temperature (or “total
air temperature”) is negligible. The density altitude (Den) is now
displayed.

NOTE: If a compatible air data system is interfaced to the KLN89(B),
the Other 12 (OTH 12) page displays pressure and density altitude
directly for the present conditions.

4.5.6.

THE CALCULATOR 6 (CAL 6) PAGE

The CAL 6 page is used to determine the true airspeed (TAS) of the
aircraft.

To calculate the true airspeed (TAS):

1

Turn on the cursor (

B

).

2.

Enter the aircraft’s calibrated airspeed by using the right inner

KLN 89/KLN 89B Pilot’s Guide

4-27

Chapter 4

APT VOR NDB INT USR ACT NAV FPL CAL SET OTH

åå.ånm| DENSITY ALT
ееееее|Prs: 05500ft
Leg|Temp: 006°C

*CRSR*|Den 05700ft

Figure 4-88

APT VOR NDB INT USR ACT NAV FPL CAL SET OTH

åå.ånm| DENSITY ALT
ееееее|Prs: 05500ft

Leg|Temp: 010°C
*CRSR*|Den 06200ft

Figure 4-87