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Figure 3-18.Automatic lubrication system
Cable Anchor Damper Installation

Aviation Boatswains Mate E - Aviation theories and other practices
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CABLE ANCHOR DAMPER LEARNING   OBJECTIVE: Describe the components of the cable anchor damper. The  cable  anchor  damper  installation  consists  of two identical anchor damper assemblies. In most cases one  cable  anchor  damper  assembly  is  deck  mounted and  the  second  assembly  is  overhead  mounted  (fig. 3-20). Compartment configuration determines how the units are installed. The  purpose  of  the  cable  anchor  damper  is  to eliminate  excessive  purchase  cable  slack  between  the crosshead and fixed sheave assembly at the beginning of   the   arrestment   stroke.   Through   service   use   and experimental testing, it was found that when this cable slack  was  taken  up  by  the  landing  aircraft,  excessive vibrations  occurred  in  the  engines.  The  cable  anchor damper   removes   this   slack   as   it   occurs,   thereby eliminating vibration of the purchase cable. The cable anchor damper assembly is used with pendant engines only. Referring   to   figure   3-20,   note   that   each   cable anchor   damper   assembly   includes   a   cylinder   that connects to an operating end head and a cushioning end head.   Piping   connects   the   engine   cylinder   to   the operating  end  head  through  a manifold  tee.  Two lines branch  from  the  manifold  tee,  one  to  each  damper assembly operating head. Each of these lines contains a flow control valve. A cover is placed over the operating piston   rod   and   coupling   assembly   for   safety   of operation  and  protection  against  foreign  matter.  Each damper    assembly    is    mounted    on    a    base    before installation. A  battery  positioner,  actuated  by  the  retracting lever,  is  provided  to  ensure  the  return  of  the  damper assembly to the BATTERY position after an arrestment. A battery-position indicator is provided to indicate   when   the   cable   anchor   damper   is   in   the BATTERY  position,  ready  for  aircraft  engagement. The limit switch and cam actuator for the battery-position   indicator   are   located   on   the   cable anchor  damper  assembly,  and  the  indicator  lights  are located on the arresting engine control panel. The  end  of  the  purchase  cable  is  attached  to  the operating end piston rod by an anchor damper coupling. When the force on the operating piston, due to engine cylinder pressure, is greater than the tensile force in the purchase   cable,   the   piston   moves   away   from   its BATTERY position. Movement of the operating piston into the cylinder removes the cable slack during the first portion of the arrestment. When the slack is taken up, the operating piston resists the return of the cable, thus keeping it taut and preventing excessive cable vibration. 3-21 MONITOR TIMER (DETAIL A) COUNTER (DETAIL B) ON/OFF SWITCH FAULT (RED) MANUAL RUN READY (GREEN) RESET LUBE (AMBER) LUBRICANT CONTROLLER RED CYCLE PROGRESS POINTER REGISTERS COUNTS REMAINING TRAVELS TO "0" DURING COUNT ORANGE CYCLE PROGRESS POINTER REGISTERS TIME REMAINING TRAVELS TO "0" DURING COUNT LOCKING SCREW LOCKING SCREW BLACK TIME SET POINTER HAS FULL SCALE ADJUSTABILITY THROUGH 320o BLACK SET POINTER HAS FULL SCALE ADJUSTABILITY THROUGH 320o DETAIL A DETAIL B ABEf0319 Figure 3-19.—Automatic lubrication controller.







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