Cessna 210B - Read before Working Loading Problem; Section V - Operating Limitations; Engine Instrument Markings; Engine Operation Limitations

Operating Limitations
...... . . 190 MPH
Maximum Structural Cruising Speed
(Le v el flight or climb)
.65-190 MPH (green arc)
Normal Op e rating Range .....
.160 MPH
Maximum Speed, Gear Extended .
Maximum Speed, Flaps Extended
Flaps 10°. . . . . . ..... . . 160 MPH
Flaps 10° _ 40° . . . .. . .... 110 MPH
Flap Operating Range. .57-110 MPH (white arc)
Maneuvering Speed* . . . . . . . .132 MPH
* The maximum speed at which abrupt control travel
can be used without exceeding the design load factor.
EN GINE OPERATI ON LIM IT ATIONS.
Power and Speed. . . ... . ....... 260 BHP at 2625 RPM
EN GINE INSTRUM ENT MARKI NG S.
OIL TEMPERATURE INDICATOR
.
Green Arc
Normal Operating Range
Red Line
Do not exceed . . . . . . .
OIL PRESSURE GAGE
· . 10
psi (red line)
Idling Pressure . .
30-60 psi (green ar c)
Normal Operating Range
· . 100 psi (red lin e)
Maximum Pressure
MANIFOLD PRESSURE GAG 'E
.15-24 in. Hg (green ar c)
Normal Operating Range . .
CYLINDER HEAD TEMPERATURE GAGE
.300-460°F (green a rc)
Normal Operating Range
. . . . 460° (red l ine )
Do Not
Exceed. . . . . . . . . . .
TACHOMETER
.2200-2450 rpm (gre en arc)
Normal Operating Range
Maximum (Engine rated speed)
2625 rpm (re d lin e) ·
FUEl QUANTITY INDICATORS
Empty (.7 gallon unusable each tank) .
· . . . E
(red line)
Operating Limitations
FUEl HOW INDICATOR
Normal Operating Ran ge . .... 8.75 - 14.13 gal/hI' (g reen arc)
Minimum and Maximum . . . . .2.0 and 21. 7 ga l/ hI' (red lines)
Maximum Performance Take - Off and Climb Settings at Altitude:
Sea Level. 19.5 ga l/ hI' (white radial)
4000 Ft. 17. 6 ga l/ hI' (white radial)
8000 Ft. . . . . . . . . . . . . 15.8 g al / hI' (white radial)
WEIGHT AND BALANCE.
The information presented in this section will enable you to operate
your Cessna within the prescribed weight and center of gravity limitations.
In figuring your loading problems be certain that you use the Licensed
Empty Weight of your particular airplane as shown on its Weight and Balance
Data sheet. This sheet, plus an Equipment List, is included with each
airplane as it leaves the factory. The FAA requires that any change in the
original equipment affecting the empty weight center of gravity be recorded
on a Repair and Alteration Form FAA-337.
READ BEFORE WORKING LOADING PROBLEM FOR YOUR AIRP LANE
To figure the weight for your airplane in the same manner
as the sample problem on page 5-4 , proceed as follows:
Step 1. Take the licensed Empty Weight and Moment / lOOO from the Weight
and Balance Data Sheet , plus any changes noted on forms FAA-337 ,
carried in your airplane and write them down in two columns in the
manner shown in the sample problem. These figures are non-
variables and, unless your airplane or equipment if modified , these
figures may be used every time you figure your weight and balance.
Step 2. Write down the weight and moment / lOOO for the oil in the proper
columns. Since you usually have a full load of oil for a trip, you
figure 12 qts. at 22.5 lbs. and a moment of -0.4. You may use
these same figures every time and consider this also a non-variable.
Step 3. Add the weight of yourself and the front passenger. Refer to the
Loading Graph on page 5-5 and find this weight at the left side of the
graph, then go across the graph horizontally to the right until you
intersect the line identified as "PILOT AND FRONT PASSENGER."
After intersecting the line , drop down vertically to the bottom line
and read the moment / lOOO given on the scale. Now write down th is
weight
and moment / 1000 foryOJ and the front passenger in the p rop er
columns.
5-2
5- 3