TM 1-1510-225-10 3B-5 VOICE, located on the copilot’s sidewall circuit breaker panel. b. Controls, Indicators, and Functions.Refer to Figure 3B-2. (1) Go-No-Go Self-Test Meter. Provides visual indication of Go-No-Go during preflight self-test. (2) TEST Switch. Allows testing of recording mode. Meter indicates self-test Go/No -Go indication and an aural tone is produced through headset jack. (3) ERASE Switch. Permits erasure of recording at end of flight. To prevent accidental erasure, the switch must be held for 2 seconds with the landing gear extended and the weight of the aircraft on the landing gear and the parking brake set. (4) HEADSET Jack . Allows monitoring of voice recordings, after a 2-second delay, and an aural tone during self-test. 3B-12. FLIGHT DATA RECORDER OSA . a. Description.The digital flight data recorder system (referred to herein as a crash data recorder) continuously records flight data inputs for the last 25 hours of flight. The flight data parameters recorded are heading, altitude, vertical acceleration, and airspeed. The data is recorded on a continuous loop, ¼ inch, self -lubricating magnetic tape bundle. The tape is drawn out of the hub and returned to the supply reel at the outer periphery of the bundle after having passed the write and read heads. The tape capsule is protected by an inner aluminum casing, an isothermal shield, an outer stainless steel casing, and an outside steel dust cover. The construction of the cases provide survivability assurance, while the isothermal shield provides protection from temperatures. There are no pilot accessible controls or switches associated with the recorder. Its operation is completely automatic. An impact switch, mounted in the aft avionics compartment, controls power to the recorder. If the impact switch is subjected to a 2.5 G shock, the recorder is electrically disconnected to prevent further recording and erasure. A red light located on the impact switch case when illuminated indicates the switch has been actuated. Pressing the reset button located adjacent to the impact switch light causes the light to extinguish and restores power to the recorder.b. Power.The recorder system is powered through a 1-ampere 115 Vac circuit breaker, placarded RECORDER POWER / FLTlocated on the copilot’s sidewall circuit breaker panel.c. Underwater Locator.A battery powered, acoustic underwater locator beacon assembly is mounted on the front panel of the crash data recorder. The unit consists of a self-contained battery, an electronic module, and a transducer. The battery is shock mounted and is separated from the electronic module by a bulkhead in the case. The beacon (pinger) radiates a pulsed acoustic signal into the surrounding water upon activation of its water-sensitive switch, and will activate automatically on submersion in salt or fresh water with an operating life expectancy of 30 days to a depth of 20,000 feet. 1. Meter 2. TEST Switch 3. ERASE Switch 4. HEADSET Jack Figure 3B-2. Cockpit Voice Recorder Control UnitOSASection III. NAVIGATION3B-13. NAVIGATION EQUIPMENT GROUP. The navigation equipment group provides the pilot and copilot with instrumentation required to establish and maintain an accurate flight course and position, and to make an instrument approach under Instrument Meteorological Conditions (IMC). The navigation configuration includes equipment for determining attitude, position, destination range; and bearing, heading reference, and ground speed. 3B-14. FLIGHT DISPLAY SYSTEM (FDS -255). a. System Overview.The Flight Display System (FDS-255), is a replacement for existing electromechanical Attitude Direction Indicator (ADI) and Horizontal Situation Indicator (HSI) flight instruments. The top and bottom displays are physically identical. The top display is configured as an
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