Installation Instructions

190-01007-A3 GTN 6XX/7XX AML STC Installation Manual
Rev. 4 Page 7-1
7 LIMITATIONS
Limitations for specific aircraft models can be found in Appendix H.
7.1 Operational Limitations
7.1.1 Operations
There are no Part 23 aircraft type limitations. All functions of the GTN unit meet the appropriate primary
or secondary design assurance qualifications for airplane Class I, Class II, Class III, and Class IV in
accordance with AC 23.1309-1E Figure 2. The TSO authorizations with the RTCA/DO-178B software
levels by function are listed in GTN 725/750 TSO Installation Manual, P/N 190-01007-02, and
GTN 625/635/650 TSO Installation Manual, P/N 190-01004-02, as well as the GMA 35 Installation
Manual, P/N 190-00858-11.
Data for some aircraft models listed on the AML is currently insufficient to substantiate IFR operations
with the GTN. Consequently, these aircraft models are limited to VFR operation only and must be
placarded in accordance with Section 2.4.1.1. Refer to Table G-1 in Appendix G to determine if a
particular aircraft model is limited to VFR when modified with the installation of the GTN.
7.1.2 Previous Operational Approvals
The installation of a GTN unit or GMA 35 Audio Panel into an aircraft does not alter the operational
approvals previously granted to that aircraft. Additional operational approvals may require FAA
evaluation of all the systems installed in a particular aircraft and is outside the scope of the
GTN AML STC.
7.2 Installation Limitations
7.2.1 Equipment Interfaced to the GTN/GMA 35 Unit
GTN 6XX/7XX or GMA 35 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.
7.2.2 Preservation of Previous Systems
It is the installer’s responsibility using data provided in this manual and data identified in the GTN AML
STC 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 GTN unit for IFR operations
requires a functional redundant electrical power system for the primary navigation unit.
7.2.3 Traffic Sensor Interfaced to the GTN
The GTN is certified to interface to no more than one traffic sensor in an aircraft. The unit supports
multiple types (GDL 88, TCAD, TAS, TCAS I, TIS) of traffic systems, but only one system may be
configured for use. Use of the GDL 88 to correlate traffic from another traffic sensor is acceptable and
does not violate this limitation. For installations with dual GTNs installed, this STC does not approve
interfacing a different traffic sensor to each GTN.
7.2.4 Major Alterations
The installation of the GTN and GMA 35 is a major alteration to the aircraft type design. Following a
major alteration, the aircraft must be returned to service in a means acceptable to the cognizant aviation
authority. An example would be an FAA Form 337 "Major Repair and Alteration Airframe, Powerplant,
Propeller, or Appliance" properly executed to describe the major alteration including the equipment and
systems to which the GTN and GMA 35 is interfaced, and submitted to the appropriate FAA office.