(8) The data from the calibration chart should be
reduced to a single value, stated as the "Test Stand C-
Factor". The "Test Stand C-Factor" will be the average
Ib/hr divided by the average cycles per sec and the
calibrated fluid specific gravity:
(Test Stand C-Factor = cps divided by cal fluid SG)
(9) The digital indicator pre-set K factor is then
determined as follows:
(a) After determining the test fuel specific gravity,
use that value times the test stand C-factor to calculate
the "K" factor.
(b) "K-factor" = Test Stand C-factor X Test fuel
(c) Temperature Compensation.
(d) (Should be the measured fuel temp minus the
calibration fluid temp) =.DF
(e) This should then be used to obtain the
corrected SP. GR. by subtracting the measured SC.
from cal fluid SG., then this difference XDF = corrected
following step are applicable to the
supply oil pressures available at the
engine oil pump with the engine not
r. Verify that the oil pressure gage (80, figure 7-8)
indicates 10 0.5 psig if a T53 engine is to be tested, or
5 0.5 psig if a T63 engine is to be tested.
s. For T73 engine test only, adjust the water in and
water out hydronic master control units in the control
cab assembly to pressurize the water brake assembly to
I. For T73 engine test only, adjust the air pressure
into the water brake assembly to 80 5 psig. For T53
engine test, adjust the air pressure into the water brake
assembly to a minimum of 20 psig.
Section III. STARTING AND OPERATING PROCEDURES
3-8. Electric Start Procedures
Ear protection must be worn by
control cab when the engine Is being
operated. Failure to observe this
warning will result in damage to and
eventual loss of hearing.
Accomplish the start of a gas turbine engine
(equipped with an electric starter) in accordance with the
Do not operate the electric starter in
excess of the specified operating
time. Allow the specified time to
elapse between attempted starts for
the dc motor to cool. Failure to
observe this precaution will result In
damage to the starter and will reduce
the service life of the batteries. Refer
to the applicable aircraft manual for
specific time limitations.
a. Depress switch 30 on data selector assembly 1A2
(7, figure 1-22), then depress the ENGINE FUEL
SOLENOID switchlight (30, figure 1-24). Verify an
indication of fuel pressure on the FUEL FLOW monitor
unit (16, figure 1-23) unit 2A2.
temperature after lightoff. Observe
the critical temperatures on the
EXHAUST GAS TEMP meter (38,
figure 1-24). Failure to observe this
precaution will result in severe
damage to the engine and equipment
and may result In serious injury due
to explosion or fire.
b. Simultaneously depress the START switch (31),
switchlight unit (35). If lightoff does not occur in the
specified time as indicated on the elapsed time indicator
(37), immediately depress the switches and the
switchlight units a second time. Allow the specified
waiting period prior to attempting a restart. If, during a
start, the temperature indicated on the EXHAUST GAS