Garmin GNS 530W, Installation Manual

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Page 7-2 500W Series Installation Manual
Rev. D 190-00357-02
7.1.2 Safety Assessment Considerations
This STC requires that the modified aircraft meet navigation and communication availability
requirements at the aircraft level appropriate to the failure conditions category, aircraft category and
class.
TSO-C146a defines loss of function of en route, terminal, non-precision approach, or precision approach
navigation data as a major failure condition. AC 23.1309-1C provides guidance for IFR airplanes that
classifies total loss of function as a major failure condition, and loss of primary means of function as
minor if two navigation systems are installed. One method to meet the major failure condition for loss of
function is to have redundant systems. It is recommended that the aircraft be equipped with at least two
independent navigation receivers and two independent communication transceivers for IFR use. For
independent navigation systems, two 500W Series units may be used, or a combination of 400W/500W
Series and an independent NAV/COM unit may be used. This will support System Safety Assessment
assumptions. Refer to AC 23.1309-1C.
7.1.3 Previous Operational Approvals
The installation of a 500W Series unit into an aircraft does not alter the operational approvals previously
granted to that aircraft. Additional operation approvals may require FAA evaluation of all the systems
installed in a particular aircraft and is outside the scope of 400W/500W Series STC SA01933LA.
7.2 Installation
The conditions and tests required for TSO approval of this article are minimum performance standards. It
is the responsibility of those installing this article either on or within a specific type or class of aircraft to
determine that the aircraft installation conditions are within the TSO standards. TSO articles must have
separate approval for installation in an aircraft. The article may be installed only if performed under 14
CFR part 43 or the applicable airworthiness requirements.
The 500W Series GPS/WAAS receiver, when installed with an appropriate antenna listed in Section
1.4.8, is compatible with aircraft equipped with SATCOM when installed in accordance to this manual.
7.2.1 GPS Antenna
The GPS/WAAS receiver is compatible with the GPS antennas listed in Section 1.4.8. Antenna selection
may affect operational limitations.
7.2.2 Antenna Installation – General
Structural mounting of the GPS/WAAS antenna is not included in this installation manual. For mounting
the GPS/WAAS antennas, refer to the Garmin GA Antenna AML STC SA01695SE or other FAA
approved installation data.
7.2.3 Equipment Interfaced to the 500W Series Unit
500W Series unit interfaces to aircraft systems other than those identified in this installation manual are
outside the scope of this manual and may require further evaluation for certification and/or other FAA
airworthiness approval.
7.2.4 Preservation of Previous Systems
It is the installer’s responsibility using data provided in this manual identified in 400W/500W Series
AML STC SA01933LA to preserve the essential characteristics of the aircraft in accordance with the
aircraft manufacturer’s original design and the requirements of 14 CFR part 23. This includes the
preservation of multiple power buses, which reduce the probability of interrupting power to essential
instruments and avionics. For aircraft certified under 14 CFR part 23, post amendment 41, use of the
500W Series unit for IFR operations requires a functional redundant electrical power system for the
primary navigation unit.