Piper Turbo Saratoga PA-32-301T Pilot's Manual page 111

PIPER
AIRCRAFT
CORPORATION SECTION
5
PA-32-301T,
TURBO SARATOGA
PERFORMANCE
NOTE
The remainder of the performance charts
used
in this flight plan example
assume a no
wind
condition. The effect of winds aloft must
be
considered
by
the
pilot when computing climb,
cruise
and descent performance.
(c)
Climb
The next step in
the
flight
plan is
to
determine the necessary
climb segment components.
The desired
cruise pressure altitude and corresponding cruise
outside air
temperature
values are the first variables
to
be
considered in determining
the
climb
components
from the Fuel,
Distance,
and Time
to
Climb
graph
(Figure 5-23). After
the fuel,
distance and time for the cruise pressure altitude
and outside air
temperature
values have been
established,
apply the existing
conditions
at
the departure field
to
graph
(Figure
5-23). Now,
subtract the values
obtained
from the. graph for the field of
departure
conditions
from those for
the cruise
pressure
altitude.
The remaining values are the true
fuel, distance and time
components
for the
climb segment of the flight plan corrected
for
field pressure altitude and temperature.
The following values
were
determined
from
the above
instructions in the flight
planning
example.
(1)
Cruise
Pressure
Altitude
12000 ft.
(2)
Cruise OAT
O° C
(3)
Time to
Climb
(14.0
min. minus
l.5
min.)
12.5
min.*
(4)
Distance
to
Climb
(20.0
nautical miles minus
2 nautical miles)
18.0 nautical miles*
(5)
Fuel to Climb
(7.5
gal
minus
.5
gal.)
7.0
gal.*
*reference
Figure
5-23
ISSUED: JANUARY
10, 1980
REPORT: VB-1070
REVISED: AUGUST 6, 1982
5-5