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 2-2
The equipment should be installed in the aircraft in a manner consistent with acceptable
workmanship and engineering practices and in accordance with the instructions set forth
in this publication. To ensure that the system has been properly and safely installed in the
aircraft, the installer should make a through visual inspection and conduct an overall
operational check of the system on the ground prior to flight.
workmanship and engineering practices and in accordance with the instructions set forth
in this publication. To ensure that the system has been properly and safely installed in the
aircraft, the installer should make a through visual inspection and conduct an overall
operational check of the system on the ground prior to flight.
The installation should be in accordance with standards established by the customer’s
installing agency and existing conditions as to unit location and type of installation;
however, the following should be considered before installing the system in order to
assure a more satisfactory performance from the equipment.
installing agency and existing conditions as to unit location and type of installation;
however, the following should be considered before installing the system in order to
assure a more satisfactory performance from the equipment.
NOTE: The TSO identifies the minimum performance standards, tests, and other
conditions applicable for issuance of design and production approval of the
article. The TSO applicant is responsible for documenting all limitations and
conditions suitable for installation of the article. An applicant requesting approval
for installation of the article within a specific type or class of product is responsible
for determining environmental and functional compatibility.
article. The TSO applicant is responsible for documenting all limitations and
conditions suitable for installation of the article. An applicant requesting approval
for installation of the article within a specific type or class of product is responsible
for determining environmental and functional compatibility.
Care should be exercised to avoid mounting components near equipment operating with
high pulse current or high power outputs such as radar and satellite communications
equipment. In general, the equipment should be installed in a location convenient for
operation, inspection, and maintenance, and in an area consistent with the TSO
environmental limits. Determine the mounting location for system components following
the guidelines below.
high pulse current or high power outputs such as radar and satellite communications
equipment. In general, the equipment should be installed in a location convenient for
operation, inspection, and maintenance, and in an area consistent with the TSO
environmental limits. Determine the mounting location for system components following
the guidelines below.
2.3.2.1 MOUNTING TRAY LOCATION(S)
The KTR 2280 MMDR mounting tray is blind-mounted behind the APEX cockpit panel
configuration.
configuration.
2.3.2.2 ANTENNA(S)
The antenna(s) should be well removed from other antenna projections, the engine(s),
and propeller(s). It should also be well removed from landing gear doors, access doors,
or other openings which will break the ground plane for the antenna(s). On metal skinned
aircraft, the antenna(s) should be bonded to the surface of the aircraft in a fore to aft
location that provides the flattest ground plane. On composite aircraft, the antenna(s)
should be a located at the center of a conductive ground plane, contoured to the shape of
the aircraft, having dimensions of at least 2 feet by 2 feet. The antenna penetration should
be designed such that the structural integrity of the fuselage is not compromised.
and propeller(s). It should also be well removed from landing gear doors, access doors,
or other openings which will break the ground plane for the antenna(s). On metal skinned
aircraft, the antenna(s) should be bonded to the surface of the aircraft in a fore to aft
location that provides the flattest ground plane. On composite aircraft, the antenna(s)
should be a located at the center of a conductive ground plane, contoured to the shape of
the aircraft, having dimensions of at least 2 feet by 2 feet. The antenna penetration should
be designed such that the structural integrity of the fuselage is not compromised.
The antenna(s) need to be within 5 degrees of the centerline
Where practical, plan the antenna location(s) to keep cable lengths as short as possible
and avoid sharp bends in the cable to minimize the VSWR.
and avoid sharp bends in the cable to minimize the VSWR.