TM 55-4920-394-13&P
CAUTION
Do not exceed the rated gpm of the individual system aircraft pumps.
Refer to the applicable aircraft publication for flow capacities of the
respective systems.
2-14. Aircraft Testing Procedures. To test an aircraft hydraulic system, proceed as follows:
a.
Perform all procedures described in paragraphs 2-2 through 2-5. If the aircraft system has been
drained, fill and air bleed the aircraft system as described in paragraph 2-13.
CAUTION
If the warning horn sounds, refer to Chapter 3, Section IV for trouble
shooting before attempting to operate the test stand for testing an aircraft
system.
b.
Open the FLOW CONTROL valve (22).
c.
Slowly close the FLUID BYPASS valve (24).
d.
Position RESERVOIR SELECTOR valve (28) as required per the applicable aircraft publication.
e.
Proceed with tests in accordance with the applicable aircraft publication.
f.
System output pressure is indicated by the output pressure gage (2). To vary the output pressure,
refer to paragraph 2-6.
g.
System volume is indicated by the flowmeter (1). To vary the output volume, refer to paragraph
h.
Fluid temperature is indicated by the FLUID TEMPERATURE gage (31).
i.
To check the return pressure from the aircraft, set the PRESSURE SELECTOR valve (6) to the
return position.
j.
To operate return back pressure system on aircraft with this requirement, set PRESSURE
SELECTOR valve (6) to back pressure position. Close return flow control valve (37, fig. 1-5). Back
pressure may be adjusted at back pressure relief valve (35, fig.1-5).
k.
Shut down test stand after test (para. 2-7).
2-11/(2-12 blank)
