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gauge pressure fitting to the metered pressure
swivel tee using a hose of sufficient length to
provide clearance from the aircraft and propeller
arc. Connect an equal length of hose to the
"suction" side of the gauge and connect to a
location to reference turbocharger compressor
discharge (upper deck) pressure. Torque all
connections.
10. Position the throttle control in the FULL OPEN
position and the mixture control to FULL RICH.
Operate the aircraft boost pump in accordance
with the aircraft manufacturer's instructions.
Following the instructions provided with the
Porta Test Unit, bleed all air from the test unit
and hoses. If using the alternative calibrated test
gauges, loosen the test connections at each
gauge to bleed the lines of any air. Operate the
boost pump only long enough to allow purging
of air from the installed test equipment. Verify
that all fuel lines, hoses and fittings are secured
and torqued and that no fuel leaks exist before
proceeding. Insure test hoses have been routed
clear of the exhaust system and are supported
their entire length to preclude inaccurate gauge
readings.
WARNING
Make certain all fuel has drained from the
induction system prior to attempting engine
start. Failure to do so could cause hydraulic
lock and subsequent engine failure.
11. Install the engine cowling or cooling shroud
during ground operation.
12. The Operational Test Form on page 19-10 may
be reproduced for use in recording adjustments
and test indications. Record the applicable IDLE
and FULL POWER adjustment points: RPM,
fuel pressure, fuel flows, manifold pressure and
fuel/air mixture rise from "Test Operating
Limits" in section 2, chapter 1 and Aircraft
Maintenance Manual on the operational test
form. See section 1, chapter 4, for:
13. Constant Speed Sea Level Performance Curve
14. Fuel Flow Vs. Brake Horsepower Performance
Curve
19-6
15. Fuel Flow Vs. Metered Pressure Performance
Curve
NOTE...
To insure optimum cooling during FULL POWER
operations, the FULL POWER fuel flow should be
set to the maximum specification limit.
WARNING
Before starting the engine insure that the
aircraft wheels are chocked and brakes are
set.
Prepare the aircraft for ground run and start the
engine
in
accordance
manufacturer's instructions.
Advance the throttle to 1500 to 1800 RPM.
While monitoring all engine gauges, operate the
engine
at
this
temperatures and pressures have stabilized in the
operational range. Use the operational test form
to record the gauge indications.
13. With the mixture control in the FULL RICH
position, reduce the throttle to the specified
IDLE RPM.
Record the unmetered pressure
indicated on the gauge.
mixture control toward the IDLE CUT-OFF
position and record the maximum RPM rise.
Return the mixture control to FULL RICH.
14. Monitoring all engine gauges, slowly advance
the throttle control to full rated power for the
engine and allow the engine to stabilize for 15
seconds. Record all engine and test gauge
indications.
DO NOT ALLOW ENGINE
TEMPERATURES
COOLANT TEMP. AND 210°F OIL TEMP.
Retard throttle control to 800 to 1000 RPM.
If the engine will not achieve full power rpm
during static ground operational test run use
Table 19-1 to correct the metered fuel pressure
specification for the actual rpm achieved.
with
the
aircraft
speed
until
the
engine
Slowly move the
TO
EXCEED
230°F
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