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Exterior Lighting
Commanders have one of the best exterior lighting signatures in the industry. Navigation lights are installed on each wing tip and the aft end of the tailcone. Anti-collision lights (three) are standard on the airplane and are located on each wing tip and at the end of the tailcone. A flashing beacon is enclosed in the forward tip of the
vertical fin. Courtesy boarding lights are standard and can be found aft the trailing edge of the flap (both sides) above the wing step. They have a three minute time delay switch that is connected directly to the battery. The courtesy lights can be operated from the cabin, or by a remote switch located above the wing step attaching plate (pilot's side).
Commander aircraft will be equipped with landing
lights located in the leading edge of each wing, and taxi lights mounted on each
main landing gear. Together, they provide 800 watts producing 350,000 candle
power to fully illuminate the pilot's field of vision.
Standard interior lighting consist of four individual overhead, push button reading lights, baggage compartment light, control wheel map reading lights, and instrument panel lighting. Instrument panel illumination is provided by blue/white flood light units installed on the under side of the glare shield. The instrument sub-panel rocker switches are illuminated by backlighting. This ample lighting package reduces shadowing and provides many lighting options for pilot and passengers.
Pitot Heat
A heated pitot tube is located near the center of the left wing on the lower surface. Tubing for the system is routed from the pitot head, aft of the spar structure, inboard to the wing root and into the cabin. A drain is located approximately eight inches left of the airplane centerline, immediately aft of the spar. Pitot heat is controlled by a circuit breaker switch labeled PITOT HEAT, located in the lower center of the instrument sub-panel.
Static System
Static ports are located on both sides of the fuselage aft of the baggage compartment. They provide normal static pressure to the aircraft systems. Tubing for the static pressure ports is routed from the static ports, up to the centerline of the rear fuselage then forward under cabin upholstery to the windshield area. The line is then routed to the alternate static valve (which also doubles as a drain), then to the instrument panel where it is coupled to the altimeter, airspeed, and VSI indicators.
Alternate Static System
An alternate static source valve (toggle-type) is installed in the lower left corner of the instrument panel. In the event the static ports become obstructed (causing erroneous static pressure instrument readings), the alternate static source provides an alternate source of static pressure.
Stall Warning System
A stall warning lift detector switch is located in the leading edge of the left wing. The lift detector switch is set to activate the stall warning horn at five to ten knots above stalling speed. The stall warning horn is located on the firewall in the cabin area. A spring-loaded test switch (located in the left main gear wheel well) allows the stall warning system to be checked with the airplane on the ground.
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