Review of the E6-B Flight Computer
It's a typhoon day, I'm at home with nothing to do, so I took out my flight computer E6-B, which I haven't used in years, to brush up on it.
I couldn't remember how to use many of the functions, so I organized them on a Google spreadsheet to see if it would be easier to understand.
Function
Calculation Content
Outer Scale
Outer Arrow/Mark
Disc Arrow
Inner Scale/Disc Scale
1
Relationship between Speed, Flight Time, and Distance
Distance 564nm
-
RATE points to outer scale Speed 125kt
Time 4.5h
2
Fuel Consumption
Fuel Amount 64gal
-
RATE points to outer scale Fuel Consumption Rate 8.4gal/h
Flight Time 7h37m
3
Climb Rate
Climb Rate 450ft/min
-
RATE points to outer scale Speed 90kt
Climb Height per NM 300ft
4
Unit Conversion NM - SM - KM
-
NAUT
STAT
KM-
Nautical Miles 10
Statute Miles 11.5
Kilometers 18.5
5
Unit Conversion US Gal - Imp Gal
-
U.S. GAL
IMP. GAL-
US Gallons 20
Imperial Gallons 16.6
6
Fuel Weight 192lbs
FUEL LBS.
U.S. GAL
US Gallons 32
7
Oil Weight 90lbs
OIL LBS.
U.S. GAL
US Gallons 12
8
Unit Conversion Lbs - KG
2000lbs
LBS
KG
901kg
9
Unit Conversion Liters - Gallons
50 Liters
LITERS
U.S. GAL
13.2 Gallons
10
Unit Conversion Feet - Meters
985ft
FT
METERS
300m
11
Unit Conversion TAS of Mach 1
TAS 660kt
-
PRESSURE ALTITUDE points to MACH NO INDEX, e.g. 15°C
1 Mach, fixed at10
12
Airspeed Correction
Calculate TAS/Density Altitude based on IAS/Air Temp/Pressure Altitude
(Altimeter pressure setting adjusted to 29.92)TAS 183kt
-
Right side AIR TEMPERATURE -15°C
Right side PRESSURE ALTITUDE 10K
DENSITY ALTITUDE 15KIAS 145kt
13
Altitude Correction
Calculate Field True Altitude MSL
※When outside air temperature is lower than standard atmospheric temperature (15.0°C), the altitude indicated will be higher than actual altitude
1. Adjust pressure setting to 29.92 to get Pressure Altitude (QNE)
2. Adjust pressure setting to Station QNH to get Corrected Altitude
3. Corrected Altitude - Field Elevation = AGL Uncorrected Height Diff
4. MSL = AGL Corrected Height Diff + Field ElevationAGL Corrected Height Diff 6600ft
-
Left side AIR TEMPERATURE -19°C
Left side PRESSURE ALTITUDE 10KAGL Uncorrected Height Diff 7000ft
14
Track Correction
Track Correction Calculation
1. Calculate Drift Angle based on flown NM and current deviation distance
2. Calculate Drift Correction Angle based on remaining distance NM and current deviation distance
3. Total Correction = Drift Angle + Drift Correction Angle = 3.8 + 2.4 = 6.2°1 Deviation Distance 8nm
2 Deviation Distance 8nm-
1 RATE points to Drift Angle 3.8
2 RATE points to Drift Correction Angle 2.41 Flown NM 125
2 Remaining Distance NM 235