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AFS-640

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AFS-640 ( afs-640 )

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AC 43.13-1B CHG 1 9/27/01 be degraded by lightning activity, airframe charging, ignition noise and atmospheric phe­ nomena. 12-14. INSTRUMENT LANDING SYSTEMS (ILS). The ILS consist of several components, such as the localizer, glide slope, marker beacon, radio altimeter, and DME. Localizer and glide slope receivers and marker beacons will be discussed in this section. a. Localizer receiver operates on one of 40 ILS channels within the frequency range of 108.10 to 111.95 MHz (odd tens). These sig­ nals provide course guidance to the pilot to the runway centerline through the lateral dis­ placement of the VOR/localizer (LOC) devia­ tion indicator. The ground transmitter is sighted at the far end of the runway and pro­ vides a valid signal from a distance of 18 NM from the transmitter. The indication gives a full fly left/right deviation of 700 feet at the runway threshold. Identification of the trans­ mitter is in International Morse Code and con­ sists of a three letter identifier preceded by the Morse Code letter I (two dots). The localizer function is usually integral with the VOR sys­ tem, and when maintenance is performed on the VOR unit, the localizer is also included. The accuracy of the system can be effectively evaluated through normal flight operations if evaluated during visual meteorological condi­ tions. Any determination of airworthiness af­ ter reinstallation before instrument flight must be accomplished with ground test equipment. b. The glide slope receiver operates on one of 40 channels within the frequency range 329.15 MHz, to 335.00 MHz. The glide slope transmitter is located between 750 feet and 1250 feet from the approach end of the runway and offset 250 to 650 feet. In the absence of questionable performance, periodic functional flight checks of the glide slope system would be an acceptable way to ensure continued sys­ tem performance. The functional flight test must be conducted under visual flight rules (VFR) conditions. A failed or misleading system must be serviced by an appropriately- rated repair station. Ground test equipment can be used to verify glide slope operation. c. Localizer/Glide Slope (LOC/GS) may have self test function, otherwise the proper ground test equipment must be used. Refer to manufacturer’s or aircraft instruction manual. 12-15. MARKER BEACON. Marker bea­ con receivers operate at 75 MHz and sense the audio signature of each of the three types of beacons. The marker beacon receiver is not tunable. The blue outer marker light illumi­ nates when the receiver acquires a 75 MHz signal modulated with 400 Hz, an amber mid­ dle marker light for a 75 MHz signal modu­ lated with 1300 Hz and, a white inner marker light for a 75 MHz signal modulated with 3000 Hz. The marker beacon system must be operationally evaluated in VFR when an ILS runway is available. The receiver sensitivity switch must be placed in LOW SENSE (the normal setting). Marker audio must be ade­ quate. Ground test equipment must be used to verify marker beacon operation. Marker bea­ con with self test feature, verify lamps, audio and lamp dimming. 12-16. LONG RANGE NAVIGATION (LORAN). The LORAN has been an effective alternative to Rho/Theta R-Nav systems. Hy­ perbolic systems require waypoint designation in terms of latitude and longitude, unlike original R-Nav (distance navigation) systems, which define waypoints in terms of distance (Rho) and angle (Theta) from established VOR or Tacan facilities. Accuracy is better than the VOR/Tacan system but LORAN is more prone to problems with precipitation static. Proper bonding of aircraft structure and the use of high-quality static wicks will not only produce improved LORAN system performance, but can also benefit the very high frequency Page 12-6 Par 12-13

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