Cessna 402C - Page 116

~Oi,402C
ALTIMETER CORRECTION -
SECTION 5
PERFORMANCE
NORMAL STATIC SOURCE
NOTE:
1. Add correction to indicated altimeter reading.
2.
The following calibrations are valid for the pilot's and copilot's
altimeters when the standard or optional dual static system is
installed.
Altitude
Sea Level
10,000 Feet 20,000 Feet
Gear
Up Down Down Up
Down Down Up
Down
Down
Flaps
0° 15° 45°
0°
15° 45°
0°
15°
45°
KIAS
Feet Feet Feet Feet Feet Feet
Feet Feet
Feet
80
7 0
0
10 0 0
13 0 0
95'
-17
-23
-32
100
-9 -9
-18 -12 -12 -24
-17 -17 -34
120 -22 22
-43 -29 "29
58
-41 -41
-81
140
-38 -38 -51 -51
-51 -69
-71 -71
-95
160 -44 -58
---
-59 -79
---
-82 -109 ---
180 -83
--- ---
-112 ---
---
-155
--- ---
200
-93
--- ---
-125
--- ---
-174
---
---
220 -82
---
---
-111
-- ---
-154
--- ---
*Recammended Minimum All Engines Approach Speed at 6850 Pounds With
45° Win9 Flaps.
ALTITUDE CORRECTION PROCEDURE
UNDICATED ALTITUDEl
L TO FLY J
1 November 1979
= fDESIRED AL TITUDEl
L (MSL) J
Figure 5-3
_ fAL TIMETER 1
LCORRECTIONJ
5-15
J: