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AC 43.13-1B CHG 1 reading on the altimeter instrument. The dif ference must not exceed 125 feet. 12-20. TRANSPONDERS. There are three modes (types) of transponders that can be used on various aircraft. Mode A provides a (non altitude-reporting) four-digit coded reply; Mode C provides a code reply identical to Mode A with an altitude-reporting signal; and Mode S has the same capabilities as Mode A and Mode C and responds to traffic alert and collision avoidance system (TCAS)-Equipped Aircraft. a. Ground ramp equipment must be used to demonstrate proper operation. Enough codes must be selected so that each switchpo sition is checked at least once. Low and high sensitivity operation must be checked. Identi fication operation must be checked. Altitude reporting mode must be demonstrated. Dem onstrate that the transponder system does not interfere with other systems aboard the aircraft, and that other equipment does not interfere with transponder operation. Special consid eration must be given to other pulse equip ment, such as DME and weather radar. b. All transponders must be tested every 24-calendar months, or during an annual in spection, if requested by the owner. The test must be conducted by an authorized avionics repair facility. 12-21. EMERGENCY LOCATOR TRANS- MITTERS (ELT). The ELT must be evaluated in accordance with TSO-C91a, TSO-C126 for 406 MHz ELT’s, or later TSO’s issued for ELT’s. ELT installations must be examined for potential operational problems at least once a year (section 91.207(d)). There have been numerous instances of interaction between ELT and other VHF installations. Antenna location should be as far as possible from other antennas to prevent efficiency losses. Check ELT antenna installations in close proximity to other VHF antennas for suspected interference. Antenna patterns of 9/27/01 previously installed VHF antennas could be measured after an ELT installation. Tests should be conducted during the first 5 minutes after any hour. If operational tests must be made outside of this time frame, they should be coordinated with the nearest FAA Control Tower or FSS. Tests should be no longer than three audible sweeps. 12-22. INSPECTION OF ELT. An in spection of the following must be accom plished by a properly certified person or repair station within 12-calendar months after the last inspection: a. Proper Installation. (1) Remove all interconnections to the ELT unit and ELT antenna. Visually inspect and confirm proper seating of all connector pins. Special attention should be given to co axial center conductor pins, which are prone to retracting into the connector housing. (2) Remove the ELT from the mount and inspect the mounting hardware for proper installation and security. (3) Reinstall the ELT into its mount and verify the proper direction for crash activation. Reconnect all cables. They should have some slack at each end and should be properly se cured to the airplane structure for support and protection. b. Battery Corrosion. Gain access to the ELT battery and inspect. No corrosion should be detectable. Verify the ELT battery is ap proved and check its expiration date. c. Operation of the Controls and Crash Sensor. Activate the ELT using an applied force. Consult the ELT manufacturer’s in structions before activation. The direction for mounting and force activation is indicated on Page 12-8 Par 12-20PDF Image | AFS-640
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