Piper PA-28-161 Pilot Operating Handbook page 84

PIPER AIRCRAFT CORPORATION
PA-28-161, WARRIOR II
(c) Climb
SECTION 5
PERFORMANCE
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 con-
sidered in determining the climb components from the Fuel, Time
and Distance to Climb graph (Figure 5-19). After the fuel, time and
distance for the cruise pressure altitude and outside air temperature
values have been established, apply the existing conditions at the
departure field to graph (Figure
5-19).
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, time and distance
components for the climb segment of the flight plan corrected for
field pressure altitude and temperature.
The following values were determined from the above instruc-
tions in the flight planning example.
(1)
Cruise Pressure Altitude
(2)
Cruise OAT
(3)
Time to Climb
(12.0
min. minus
3.0
min.)
(4)
Distance to Climb (
16.0
miles minus
4.0 miles)
(5)
Fuel to Climb
(3
gal. minus
1.0
gal.)
(d) Descent
5000
ft.
l6°C
9.0
min.*
12.0
miles*
2.0
gal.*
The descent data will be determined prior to the cruise data to
provide the descent distance for establishing the total cruise
distance.
Utilizing the cruise pressure al\itude and OAT, determine the
basic fuel, time and distance for descent (Figure 5-31). These figures
must be adjusted for the field pressure altitude and temperature at
the destination airport. To find the necessary adjustment values,
use the existing pressure altitude and temperature conditions at the
destination airport as variables to find the fuel, time and distance
*reference Figure 5-19
ISSUED: AUGUST 13, 1982
REPORT: VB-1180
5-5