89000004-200
KA 310 STC Installation Manual
Rev 0
4-2
© Honeywell International Inc. Do not copy without express permission of Honeywell.
indicating the LRUs added, removed or relocated along with the date of installation. Include your name
and certificate number in the aircraft records. See Table 4-1 for the KA 310 LRU weight and refer to
Figure A - 3 for the KA 310 center of gravity. The weight and balance computation should also include
the weight of additional wiring and installation hardware for the KA 310.
Table 4-1: KA 310 LRU Weight
LRU
Weight (lbs.)
KA 310 Base Unit
1.07 lbs.
4.3
Cable and Wiring
Refer to APPENDIX B for the appropriate wiring connections and installation options to assemble the KA
310 wiring harness. Use the connectors included in the KA 310 Installation Kit, PN 89000004-104 (Refer
to Table 3-4). Refer to Table 3-5 for wire types. Follow the cabling requirements listed in Section 3.9.
Route the wiring bundle as appropriate.
CAUTION
DO NOT ROUTE CABLE NEAR HIGH VOLTAGE SOURCES OR FLAMMABLE FLUID LINES.
4.4
Wiring, and Power Checks
Verify all cables are properly secured. Prior to powering up the KA 310, the wiring harness must be
checked for proper connections to the aircraft power bus and the KA 310. Point to point continuity
must be checked on all wiring to identify any faults such as shorting to ground. Any faults or
discrepancies must be corrected before proceeding. Upon completion of the power and ground checks,
the unit is ready for power to be applied.
4.5
Aircraft Electrical Load Analysis (ELA)
An electrical load analysis (ELA) must be completed to confirm that the aircraft electrical system can
support the KA 310. The maximum electrical system demand should not exceed 80% or maximum load
published in the AFM/ELA/AMM of the alternator(s)/generator(s) rating during normal operation.
4.5.1
Aircraft with Existing ELA
If the aircraft has an existing ELA, update the ELA to reflect the addition of the KA 310 LRU. The updated
ELA must show the alternator(s)/generator(s) have adequate capacity to supply power to the modified
systems in all anticipated conditions. The typical current draw for the KA 310 from Section 2.7 should be
added to the existing ELA under continuous operating conditions. Verify the new electrical load does not
exceed 80% or maximum load published in the ELA of the rated capacity of the installed
generator(s)/alternator(s). If the additional load of the KA 310 exceeds the rated capacity, alternate FAA
approval is required for the installation of the KA 310 in the aircraft.
REF:
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UP793797
