Quantcast FLIGHT DATA RECORDER  OSA - TM-1-1510-225-10_280

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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  /  FLT  located  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 Unit  OSA Section III.  NAVIGATION 3B-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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