b. Open the HP bypass valve.
c. Depress stop button.
d. Set all circuit breakers to off position.
2-11. Emergency shutdown. 'Should it be necessary to stop the test stand rapidly, depress stop pushbutton and open
the HP bypass valve.
2-12. Fluid sampling. A sample of hydraulic fluid may be withdrawn from the system to analyze for contamination
utilizing the LP gage test port.
SECTION III. AIRCRAFT FILL AND TEST PROCEDURES.
2-13. Positioning and connecting the test stand to aircraft. Position and connect the test stand for aircraft test as follows:
a. Move the test stand to the operating site using a suitable towing vehicle.
b. Position the test stand with respect to the aircraft so that the hoses can be connected between the aircraft and the
test stand without sharp bends or kinks.
c. Set the brakes by pulling out on the brake lever.
d. Raise the tow bar and secure it in its vertical position using 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 the fittings with solvent conforming to Federal Specification PD-680, Type II.
g. Make the necessary hose connections between the aircraft and the outlet and return fittings on either side of the
test stand. Accessory fittings and adapters for use in making aircraft connections are supplied with the test stand.
2-14. Replacing lost hydraulic fluid in an aircraft. Small quantities of fluid, such as that lost when making the hose
connections, may be replaced in an aircraft using the fill pump of the test stand. The procedures described in the
following steps should be used with the hoses connected to the aircraft. To completely fill and bleed air from an aircraft
system which has been drained, refer to paragraph 2-15.