Bedienungsanleitung Garmin GTN 650 (Seite 67 von 412) (Englisch)

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190-01007-A3 GTN 6XX/7XX AML STC Installation Manual

Rev. 4 Page 2-25

2.4.6 Placards and Labels

All placards and labels must be readable in all cockpit lighting conditions. Ambient flood lighting is

acceptable. Placards added as part of the GTN and GMA 35 installation must be displayed in a

conspicuous place and must not be easily erased, disfigured, or obscured. Text height must be a minimum

of 0.10 inch, and the text must contrast with the placard surroundings such that it is easily readable. The

text must be a high-quality, solid-color font of at least 300 DPI (dots per inch). Dot-matrix fonts are

unacceptable.

New circuit breakers and switches installed for the GTN or GMA 35 unit must be labeled as shown in the

applicable interconnect drawing in Appendix E or Appendix F.

2.4.7 Power Distribution

For the purpose of this section, an avionics bus is considered to be any group of circuit breakers fed from

a common source or multiple sources with a remote switch for the intent of controlling the power to

avionics equipment.

2.4.7.1 Circuit Protection

Circuit protection devices for the GTN and GMA 35 must be push-pull manually resettable circuit

breakers (e.g. Klixon 7274 or 7277 Series circuit breakers). Refer to Figure E-4 for GTN circuit breaker

ratings or Figure F-2 for GMA 35 circuit breaker ratings. The circuit breakers must be labeled as specified

in the interconnect diagrams in Appendix E and Appendix F and the circuit breakers must be readily

accessible to the pilot.

A single circuit breaker must be dedicated to the GTN Main and NAV power inputs as shown in

Figure E-4. A single circuit breaker must also be dedicated to the COM input for the GTN 635/650/750.

See Figure E-4 for more information. Do not combine more than one unit on the same circuit breaker.

2.4.7.2 Power Distribution – Single GTN, Aircraft Weight Less than 6000 Pounds

When one GTN is installed in aircraft with a maximum certified gross takeoff weight of less than 6000

pounds, the GTN should be connected to the avionics bus. The NAV/GPS and COM circuit breakers

(Reference Figure E-4) must be connected to the same avionics bus.

When the GTN is the second NAV/COM unit being installed in the aircraft, the GTN should be connected

to the avionics bus. The NAV/GPS and COM circuit breakers (Reference Figure E-4) must be connected

to the same avionics bus. The GTN and other NAV/COM must be grounded at separate ground

terminal/stud locations on the aircraft. The power and ground wiring for the GTN should be routed

separately from the power and ground wiring for the other NAV/COM. This method, shown in

Figure 2-11, will maximize system redundancy if the ground connection for one radio fails.

Avionics Bus

GTN 6XX/7XX

COM

Ground Plane

Other NAV/COM

Figure 2-11. Power and Ground Distribution -

Single GTN, Aircraft Weight Less Than 6000 lb

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