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RELEASED FOR THE EXCLUSIVE USE BY: AIRCRAFT ELECTRONICS ASSOCIATION
BENDIX/KING
2.7
ADAPTER INSTALLATION
2.7.1
KA 52 ADAPTER
The KA 52 is an optional remote mounted unit that converts the DC heading and course datum
signals from the KI 525/525A to AC signals compatible with certain autopilot systems.
2.7.2
MOUNTING
The KA 52 may be mounted in any convenient location with four #6 screws per Figure 2-7. It is
suggested that the unit be mounted so that it is accessible in flight in order for service personnel
to perform alignment adjustments for optimum performance. The mating connector is furnished
with the unit. Figures 2-9 and 2-10 shows a typical installation that incorporates the KA 52.
2.7.3
KA 57 ADAPTER
The KA 57 is an optional remote mounted unit that converts the DC heading and course datum
signals from the KI 525/525A into an AC signal compatible with certain autopilots that have a sin-
gle input. The KA 57 has a single output, Heading Select or Course Datum, that is determined by
the Autopilot switching.
2.7.4
MOUNTING
The KA 57 may be mounted in any convenient location with four #6 screws per Figure 2-8. It is
suggested that the unit be mounted so that it is accessible in flight in order for service personnel
to perform alignment adjustments for optimum performance. The mating connector is furnished
with the unit.
2.8
ADJUSTMENTS
2.8.1
KI 525/525A
No adjustments are required.
2.8.2
KG 102/102A
A switch located on the top surface of the KG 102/102A has a 14 volt and a 28 volt position. This
switch must be set in the position that corresponds with the input DC voltage. To change the
switch position remove the switch cover, set the switch in the desired position, then re-install the
switch cover. The correct input DC voltage (14 or 28) should then be seen through the switch cov-
er.
2.8.3
KMT 112
With the complete KCS 55/55A system operating and synchronized, position the aircraft on a com-
pass rose and turn it to each of the four cardinal headings. Place the KA 51/51A/51B in the "Free
Gyro" mode and center the slave meter with the manual slave buttons on the KA 51/51A (toggle
switches on the KA 51B) at each of these headings. Record the algebraic error between the com-
pass rose and the heading on the KI 525/525A. Add the algebraic errors and divide by four to
obtain the index error.
Loosen the mounting screws on the KMT 112 and rotate the unit an amount equal to the index
error to cancel-out the index error. Retighten the mounting screws. This procedure should be re-
peated after the N/S E/W compensator has been adjusted (see paragraph 2.8.4).
2.8.4
KA 51/51A
With the complete KCS 55/55A system operating and the KA 51/51A in the "free gyro" mode; po-
sition the aircraft on a compass rose and adjust the compensator as follows:
Page 2-4
©Honeywell International Inc. Do not print without express permission of Honeywell
KCS 55/55A
Rev 11, Apr/2007
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