True blue power TA102, Руководство по установке и эксплуатации

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6 Manual Number 9017942 • Revision K, May 14, 2020
SECTION 2 PRE-INSTALLATION CONSIDERATIONS
2.1 COOLING
No external cooling is required. The unit will become warm when in use. This is normal and within
operational parameters. No special mounting considerations are required; however, mounting to a
metal surface can help dissipate any heat generated and extend the life of the product.
2.2 EQUIPMENT LOCATION
The TA102 Dual USB Charging Port is designed for mounting flexibility, allowing for installation in
the cockpit or in the cabin. It is designed for panel mounting and can be installed in a rectangular
or circular rear mount configuration or, with an available installation kit, can be front mounted with
a cosmetic cover plate. An instrument mounting adapter bracket is also available to easily mount
the unit in a standard 2-inch round instrument opening that may already exist in the cockpit panel.
There are two versions to choose from which allow the input connector to be located either on the
rear of the unit or from the bottom.
The unit can be mounted in any orientation. Clearance should be provided for the mating
connector which may require an additional inch beyond the rear of the unit.
2.3 ROUTING OF CABLES
Avoid sharp bends in cabling and routing near aircraft control cables. Avoid close proximity and
contact with aircraft structures, avionics equipment or other obstructions that could chafe wires
during flight and cause undesirable effects.
2.4 LIMITATIONS
Environmental qualifications were verified per RTCA DO-160, Revision G in lieu of those identified
within the minimum performance standards (MPS) of the TSO.
The conditions and tests for TSO approval of this article are minimum performance standards.
Those installing this article, on or in a specific type or class of aircraft, must determine that the
aircraft installation conditions are within the TSO standards, specification of the article and
deviations as listed above. TSO articles must have separate approval for installation in an aircraft.
The article may be installed only according to 14 CFR part 43 or the applicable airworthiness
requirements.