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Page Title: 1-8.1. Cover Assembly.
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TM 1-4920-458-13&P 1-8.  LOCATION AND DESCRIPTION OF MAJOR COMPONENTS (CONT) 1-8.1. Cover Assembly. The  Tester  is  16.6  inches  long,  14.5  inches  deep  and  17.0  inches  high  when  contained  within  its  removable  cover  for transit.  The cover contains accessories necessary for proper operation of the Tester.  When the cover is removed, all operating controls, indicators, and accessories are accessible for immediate use. 1-8.2. Frame Assembly. The frame assembly of the Pitot and Static Systems Tester contains three aircraft instruments:   rate of climb, altimeter and  airspeed  indicator.    Vacuum  and  pressure  controls,  bleed  needle  values,  a  vacuum  selector  valve,  a  pressure selector  valve,  and  an  "ON-OFF"  valve  for  each  of  the  three  respective  instruments  are  also  clearly  marked  on  the control panel.  Also contained on the control panel are the on-off power switch, press to test button, and 5 amp fuse.  A spare fuse is mounted on top of the frame assembly. 1-8.3. Back Plate. The  back  plate  contains  two  ports:    A  "Static"  port  and  a  "Pitot"  port  for  hook-up  to  the  same  respective  ports  on  the aircraft.  Hoses and adapters are provided in the accessory storage compartment.  Also, a power connector is provided through which AC and DC power is supplied to the tester. 1-8.4. Interior Components. For access to interior components of Tester, captive fasteners on the control panel are released and the panel is then swung  upward  to  the  "Open"  position;  with  the  panel  open,  the  motor-pump  assembly,  oil  reservoir  assembly  and electrical  power  supply  components  are  easily  accessible  as  are  adjustable  pressure/vacuum  relief  valves,  a  system pressure relief safety valve, and all fittings and hoses.  In addition, rigid pressure lines could be removed if necessary. Located on the side of the box is a clear window, which permits observation of fluid level in the oil reservoir. 1-5

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