TM55-2840-251-23
Section X ENGINE TESTING (Continued)
1-94
GROUND TEST OF ENGINE
INSTALLED IN AIRCRAFT
(Cont)
5.
(Cont)
d.
Having determined values of these
parameters, proceed with engine performance check, as
follows:
NOTE
This check should be carried out without bleed
air on power extraction for operation of aircraft
auxiliaries.
(1)
Perform pre-start check (subparagraph
2).
(2)
Accomplish satisfactory start (refer to
TM55-1510-209-10/2.
(3)
Run engine at FLIGHT-IDLE to warm
up engine and to stabilize engine instruments.
(4)
Set propeller control lever to maximum
output speed 91% (2000 rpm) and power lever to torque
setting previously determined from engine performance
curve.
(5)
Compare observed fuel flow, gas
generator speed and interturbine temperature with values
previously recorded.
(6)
Insure that values observed during
engine performance and data plate speed check are
within the following limits:
a.
±
15 lbs. hr/fuel flow.
b.
±
2% maximum gas generator speed data
plate speed ratio. (Ratio = observed gas generator speed
- data plate speed.)
c. Interturbine temperature of ±
30°C. If
temperature is more than 30 °C below target temperature
check instrumentation.
NOTE
If observed values deviate from the preceding
limits, an instrument or engine fault is indicated
(refer to Section VII).
(7)
Carry out an engine shutdown check
(subparagraph 7).
6.
Check No. 5 - Reverse Thrust Performance
Check.
a.
This check should be carried out whenever
propeller reversing controls have been disconnected or
adjusted and whenever fuel control, power turbine
governor, or constant speed unit (propeller) have been re-
placed.
b.
Propeller reversing system is normally
adjusted to provide a flat rated power of 400 shp at all
ambient temperatures. The system may be adjusted to
provide varying reverse powers as defined in TM55-1510-
209-10/2.
c.
Information supplied by TM55-1510-209-10/2
is used to determine desired reverse power by providing
corresponding torque pressure values and related
propeller speeds.
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