CURVE NO 12881
TO FINDACTUAL
HORSEPOWER
FROMALTITUDE.
R PM..
MANFOLD PRESSURE
LYCOMING
AIRCRAFT
° AND AIR INLET
TEMPERATURE.
LYCOMING AIRCRAFT
1. LOCATE A ON FULLTHROTTLEALTITUDE CURVE FOR GIVEN R.P.M. MANIFOLD
PRESS. HELICOPTER ENGINE
2. LOCATE B ON SEALEVEL
CURVE FOR R.PM. & MANIFOLD
PRESSURE & TRANSFER TO C.
PERFORMANCE
DATA
3.CONNECT
A C BYSTRAIGHTLINEAND
-READ HORSEPOWER
AT GIVENALTITUDED
4. MODIFY HORSEPOWERATD FOR VARIATION OFAIR INETTEMPERATURE T FROM MAXIMUM POWER MIXTURE
STANDARD
ALTITUDE TEMPERATURE
T
S
UNLESS OTHERWISE
NOTED
BY
FORMULA
ALTITUDE
PERFORMANCES
ENGINE MODEL
HO-360-B SERIES
ABS.
DRY MANIFOLD
COMPRESSION
RATIO 8.5:1
W
HP AT D X
PRESSURE
IN HG
COMPRESSION RATIO
8.5:1
ACTUAL
H.P
CARBURETOR BENDIX PSH-5BD
ABSOLUTE MANIFOLD PRESSURE, IN.
Hr. PRESSURE
ALTITUDE IN THOUSANDS OF FEET
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