Performance
DA 40 NG AFM
Page 5 - 6
Rev. 3
01-Jul-2014
Doc. # 6.01.15-E
s
ta
n
d
a
rd
te
m
p
e
ra
tu
re
dens
ity
al
t. [ft]
den
sit
y al
t. [m
]
pres
sure
alti
tude
[m]
pres
su
re
al
titud
e
[ft]
temperature
-2000
14000
12000
10000
12000
14000
10000
8000
6000
4000
2000
0
8000
8000
6000
4000
2000
0
0
500
1000
1500
2000
2500
3000
3500
4000
0
500
1000
1500
2000
2500
3000
3500
4000
-20
-10
0
10
20
30
-500
32
50
68
86
14
-4
[°C]
[°F]
5.3.3 PRESSURE ALTITUDE - DENSITY ALTITUDE
Conversion from pressure altitude to density altitude.
Example:
1. Set 1,013.25 hPa on altimeter and read pressure altitude (900 ft).
2. Establish ambient temperature (+21
E
C).
3. Read off density altitude (1800 ft).
Result:
From a performance calculation standpoint the airplane is at 1800 ft.
Summary of Contents for DA 40 NG
Page 1: ......
Page 2: ...DA 40 NG AFM Introduction Page 0 0a Rev 3 01 Jul 2014 Doc 6 01 15 E Intentionally left blank...
Page 240: ...Mass Balance DA 40 NG AFM Page 6 8 Rev 3 01 Jul 2014 Doc 6 01 15 E 6 4 2 LOADING DIAGRAM...
Page 316: ...Handling DA 40 NG AFM Page 8 8 Rev 3 01 Jul 2014 Doc 6 01 15 E...
Page 322: ...Handling DA 40 NG AFM Page 8 14 Rev 3 01 Jul 2014 Doc 6 01 15 E Intentionally left blank...
