Honeywell BENDIX/KING KLN 94 - Manual (Page 82)

B
KLN 94
Rev. 4, Jan/2003 10599I04.CDL Page 2-78
Diskette Update
Connect the laptop via the PC loader kit PN 050-03612-0000 (ref figure 2-26 ). Turn on the KLN
94 to the SET 3 page. Insert the 3.5" Database diskette into the PC. Cycle the power of the PC
and follow the menu driven instructions. (A small number of PC’s may exhibit problems during the
load because a few select BIOS services are incompatible with the Honeywell diskettes. If there
is uncertainty relating to this, contact Honeywell Product Services at (913) 782-0600, or
Navigation Services at 1-800-247-0230 or (913) 712-3145.)
NOTE
The KLN 94 database may be updated using a PC with the KLN 94 mounted
in an aircraft (refer to Figure 2-18 ).
Cartography databases are only updateable via card exchange. Update frequency has not yet
been established but will most likely be annually.
2.4.4.10 ALT ALERT, ALT ALERT AUDIO
Upon approval of the self-test page, five (5) beeps will be issued on the audio output and five (5)
sonalert bursts will be produced by the ALT ALERT output, if ALT ALERT has been configured
“Enable”.
2.4.4.11 Heading Interface
Heading information may be interfaced to the KLN 94 by RS 232 to aid in the calculation of wind
vectors and for heading orientation of the NAV 4 or moving map. RS 232 heading information
may be provided from an analog to RS 232 converter, such as the Shadin fuel/air data device,
through the RS 232 input.
Display the NAV 4 page and select the HDG orientation to test the heading function. If a valid
heading source is available, HDG orientation will be selectable. Turn the cursor on the Nav 4
page to display the heading value when the HDG orientation is selected.
2.4.4.12 Flight Control Roll Steering Ground Test
NOTE
This ground test assumes that a KFC 225 Flight Control System is installed.
Ground Test is not available for other Flight Control Systems
Ensure That:
All Gyros used by the Flight Control System need to be spun up to speed and the aircraft needs
to be level in the roll axis.
The Attitude Gyro is fully erected and stabilized.
The Flight Control System has conducted and completed a successful pre-flight test.