Cessna 402C Pilot Operating Handbook 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 ALTITUDEl
L (MSL) J
Figure 5-3
_ fALTIMETER
1
LCORRECTIONJ
5-15
J: