Honeywell International Inc. KTR2280 Manuale Utente
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KTR 2280 Preliminary H 08/17/06
Rev. 0, Aug/2006
©Honeywell International Inc. Do not print without express permission of Honeywell
Page 2-6
2.3.5 ELECTRICAL INSTALLATION
2.3.5.1 KTR 2280 INTERCONNECTION AND CABLE HARNESS FABRICATION
NOTE: The only current KTR 2280 installation option is as a part of the APEX system.
For detailed interconnection information relating to a specific installation, refer to
the applicable APEX system installation manual and/or engineering bulletin (EB).
the applicable APEX system installation manual and/or engineering bulletin (EB).
The KTR 2280 MMDR receives primary power from the aircraft power source. Power
connections, voltage requirements, and circuit breaker requirements may be found in the
APEX system installation manual and/or engineering bulletin (EB) for a specific
installation.
connections, voltage requirements, and circuit breaker requirements may be found in the
APEX system installation manual and/or engineering bulletin (EB) for a specific
installation.
The length of the wires to parallel pins should be approximately the same length, so that
the best distribution of current can be effected. Honeywell recommends that all wires,
including spares, as provided with the interconnect definition information be included in
the fabrication of the wiring harness. However; if full wiring is not desired, the installer
should ensure that the minimum wiring requirements for the features and functions to be
used have been incorporated.
the best distribution of current can be effected. Honeywell recommends that all wires,
including spares, as provided with the interconnect definition information be included in
the fabrication of the wiring harness. However; if full wiring is not desired, the installer
should ensure that the minimum wiring requirements for the features and functions to be
used have been incorporated.
When cables are installed in the aircraft, they must be supported firmly enough to prevent
movement and should be carefully protected against chaffing. Additional protection
should also be provided in all locations where the cable may be subjected to abuse.
movement and should be carefully protected against chaffing. Additional protection
should also be provided in all locations where the cable may be subjected to abuse.
In wire bundles, the cabling should not be tied tightly together as this tends to increase the
possibility of noise pickup and similar interference. When routing cables through the
aircraft the cables should cross high level rf lines at right angles.
possibility of noise pickup and similar interference. When routing cables through the
aircraft the cables should cross high level rf lines at right angles.
Prior to installing any equipment, make a continuity check of all wires and cables
associated with the system. Then apply power and check for proper voltages at system
connectors, and then remove power before completing the installation.
associated with the system. Then apply power and check for proper voltages at system
connectors, and then remove power before completing the installation.
The following guidelines are recommended:
(1)
The installing facility will supply and fabricate all external cables. The re-
quired connectors are supplied as part of the installation kit (P/N
050-03451-0000).
quired connectors are supplied as part of the installation kit (P/N
050-03451-0000).
(2)
The unit must be kept a minimum of three feet from the antenna. Addition-
ally, the antenna coax cable should not be bundled with the other wiring har-
nesses to the unit.
ally, the antenna coax cable should not be bundled with the other wiring har-
nesses to the unit.
(3)
The length and routing of the external cables must be carefully planned be-
fore attempting the actual installation. Avoid sharp bends or locating the ca-
ble near aircraft control cables. The cables should be of a length to allow
for a “maintenance loop”. That is, the length should be adequate to access
and extend the connectors aft of the panel for future maintenance purposes.
Excess cabling should be secured and stowed by tie-wrapping until such
maintenance is required.
fore attempting the actual installation. Avoid sharp bends or locating the ca-
ble near aircraft control cables. The cables should be of a length to allow
for a “maintenance loop”. That is, the length should be adequate to access
and extend the connectors aft of the panel for future maintenance purposes.
Excess cabling should be secured and stowed by tie-wrapping until such
maintenance is required.