POH
AQUILA AT01-200C
Section 5
PERFORMANCE
Document Nr.:
Issue:
Supersedes Issue:
Date:
Page:
FM-AT01-1010-106
A.01
--- (first issue)
02.03.2020
5 - 20
CALCULATION OF FUEL REQUIRED
Fuel required for engine start-up and taxiing
0.8 US gal (3.0 ltr)
(General Value, see remark “Fuel Quantity”
on pg. 5-12 and 5-13)
Fuel required for climb (page 5-18)
+1.25 US gal (4.7 ltr)
2.05 US gal (7.7 ltr)
Climb distance (page 5-18)
11.9 NM
Wind correction (tailwind)
+ 1.2 NM
13.1 NM
During the descent from 9500 ft to 380 ft, a distance of 27 NM is covered and 0.44 US gal (1.65
ltr) of fuel consumed (page 5-14). The influence of the wind has been neglected.
Overall flight distance
480.0 NM
Climb distance
- 11.9 NM
Descent distance
- 27.0 NM
Cruise section
441.1 NM
With the expected 10 kts tail wind, we obtain a (estimated) ground speed of:
129 kts + 10 kts = 139 kts
for the time spent in cruise we obtain:
441.1 NM
139 kts = 3,17 h = 3 h 10 min
The fuel required for the cruise segment is:
3.17 h x 6.21 US gal/h (23.5 l/h) = 19.69 US gal (74.5 ltr)
A fuel flow of 6.21 US gal/h (23.5 l/h) is calculated from the table on page 5-11 in the section for
the power setting of 75 % MCP as follows:
Option 1: For a temperature of 32°F (0°C) at 9500 ft, we obtain a density altitude of 10000 ft
(refer to the tables on page 5-10 and 5-12). By using density altitude instead of pressure
altitude, we already accounted for the deviation from ISA conditions. An additional correction,
as shown on page 5-11, is no longer necessary as fuel consumption (6.2 US gal/h) is already
shown at density altitude.
Option 2: In order to obtain the fuel flow for the cruise altitude of 9500 ft, an interpolation has to
be conducted for the values given for 8000 ft and 10000 ft, respectively. Furthermore, the
deviation of ISA-temperature by 7.2°F (4°C) has to be accounted for by using the correction,
stated on page 5-11:
6.18 gal / h x 1.01
≈ 6.2 gal / h