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Table 2-2.  Control Settings
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TM-1-4920-446-13P Hydraulic System Test Stand Type D-8A P/N 7459 Manual
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Aircraft Testing Procedures
TM 1-4920-446-13 & P d.  Set circuit breaker CB1 to OFF position. 2-9 .   Emergency Shutdown.  If necessary to stop the test stand rapidly, depress stop pushbutton and open the HP by- pass valve (7). 2-10.  Fluid Sampling.  A  hydraulic fluid sample may  be withdrawn from the suction pressure calibration port (21). SECTION III.  AIRCRAFT FILL AND TEST PROCEDURES 2-11.  Positioning and Connecting the Test Stand to Aircraft. a.  Move the test stand to the operating site using a suitable towing vehicle. b.  Position the test stand so the hoses can be connected between the aircraft and test stand without sharp bends or kinks. c.  Set the brakes by pushing down on the brake lever. d.  Raise the tow bar and secure it in the vertical position.  Secure with the tow bar latch. e.  Remove the hoses from the hangers on which they are stored. Use volatile solvents only in a well ventilated area.  Avoid  prolonged contact with the skin. f.  Check that the connector fittings on the hoses and the outlet and return fittings on the test stand are clean.  If the fittings are dirty, wash with solvent, P-D-680, Type II. g.  Connect hoses between the aircraft and the outlet and return fittings at the rear of the test stand.  Accessory  fit- tings  and  adapters  for use in making  aircraft connections are supplied with the test stand. 2-12.  Replacing Lost Hydraulic Fluid in an Aircraft.  Small quantities of fluid, such as that lost when making the hose connections,  may  be  replaced  during  normal  operation  of  the  test  stand.    To  fill  and  bleed  air  from  an  aircraft  system which has been drained, refer to paragraph 2-13. 2-13.  Bleeding an Aircraft Hydraulic System.  If an aircraft system has been drained or the hydraulic fluid supply de- pleted, the following procedure will renew the system. NOTE Two persons are required; one to operate the test stand, the other to cycle the aircraft controls and monitor from the aircraft. 2-8

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