System Requirements
The following are strobe system recommendations. The basic model/part numbers are given. However, in some cases, the aircraft voltage and mounting location of the light are needed to specify the exact model/part number needed. Whelen does not have specific kits set up (Contact Authorized Whelen Distributors).
ANTI-COLLISION and POSITION LIGHT REQUIREMENTS, LOCATIONS, & DISTRIBUTION PATTERNS
All aircraft must have an approved anti-collision light and position light system for nighttime operations. The position lights consist of an Aviation Red on the left side, an Aviation Green on the right, and an Aviation White tail-light (REF. FAR 23.1389). *The position lights must be wired independent of the anti-collision lights.
The anti-collision lighting system is required under FAR PART 91.205(c). There are different requirements affecting different aircraft. These aircraft are categorized by the date of application for type certificate. Home built aircraft are determined by the date of issuance of the Experimental Operating Limitations. The different categories are as follows:
1. Aircraft for which type certificate was applied for after April 1, 1957 to August 10, 1971: These anti-collision systems must produce a minimum of 100 effective candela in aviation Red or White (REF. FAR 23.1397), 360° around the aircraft's vertical axis, 30° above and below the horizontal plane (REF. FAR 23.1401).
2. Aircraft for which type certificate was applied for after August 11, 1971 to July 18, 1977: These anti-collision systems must produce a minimum of 400 effective candela in aviation Red or White (REF. FAR 23.1397), 360° around the aircraft's vertical axis, 30° above and below the horizontal plane (REF. FAR 23.1401).
3. Aircraft for which type certificate was applied for after July 18, 1977: These anti-collision systems must produce a minimum of 400 effective candela in aviation Red or White (REF. FAR 23.1397), 360° around the aircraft's vertical axis, 75° above and below the horizontal plane (REF. FAR 23.1401).
INSTALLATION LOCATIONS
WINGTIP:
The installation time for wingtip strobe light systems will vary depending on the type of system being installed. Installation time can be greatly reduced if it is done in conjunction with an annual or one hundred-hour inspection. The major difference in the systems is the location of the strobe power supply. They can be mounted locally, one in each wingtip, or a single power supply mounted in the fuselage.
There has been some concern in the past with running the high voltage cable through the wings and by the fuel tanks. For there to be an explosion two conditions must be met. There must be an explosive atmosphere, and there must be a source of ignition. For there to be an explosive atmosphere inside the wing, it would require a fuel tank leaking into the wing. However, strobe power cables are not routed through the wing bays, they are routed forward or aft. Then there is the matter of spark for ignition. For this to occur there would have to be a breakdown of the cable insulation. This is very unlikely if the cable has been properly installed. The power supplies are designed to turn off when there is a short. With power supplies mounted in the wing, the input wires still need to be run to provide power to them.
FUSELAGE:
Another option is to install fuselage mounted units. They can be either self-contained, in which the power supply and light head are one unit, or remote light heads run off a separate power supply. To meet the field of coverage, one must be on the top of the fuselage & one on the bottom.
VERTICAL FIN:
Lastly if applicable, a single anti-collision light can be mounted on the vertical stabilizer. It also can be either a self-contained unit or a remote light head, depending on the aircraft.
