Cessna TURBO CENTURION T210M 1978 Owner's manual

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HAINDB00 - 1(
. --
_____ ...
.... ____ .
3-RPC-750-10/77

LIST OF EFFECTIVE PAGES
CESSNA
MODELT210M
LIST OF EFFECTIVE PAGES
INSERT LATEST REVISED
PAGES; DISPOSE OF
SUPERSEDED PAGES.
NOTE: This handbook will be kept cur rent by Service Letters published by Cessna
Air craft Company. These are distributed to Cessna Deale rs and to those who
s ub scribe through the Ow ner F ollo w -Up System. If you are no t receiving
subsc
rip tion se rvice, you will want to keep in touch with your Cessna D ea ler for
informa tion conce rning the revision status of the handbook. Subsequent
revisions should be examined
immed ia tely after receipt; the handbook should
not be used for operational purposes until it h as been updated to a current stat us .
On a revised page, the portion of the text or illus tration affected bythe revision is
indicated by a vertical
line in the outer margin of the page.
Dates
of issue for original and revised pages are:
Original ... 0 . . . 15 August 1977
THE TOTAL NUMBER OF PAGES IN THIS HANDBOOK IS 390, CONSISTING OF THE
FOLLOWING. THIS TOTAL INCLUDES THE SUPPLEMEN TS PROVIDED IN SEC T ION 9
WHICH COVER OPTIONAL SYSTEMS AVAILABLE IN THE AIRPLANE.
Page #Revis ion
Page
#Revision
No. No. No. No.
Title 0 5-32 Blank 0
A 0
6-1
0
i thru iii 0 6-2 Blank 0
iv Blank 0 6-3
thru 6-13 0
1-1
thru 1-8 0 6-14 Blank 0
2-1
0 6-15
thru 6-28 0
2-2 Blank 0
7-1 thru 7-50 0
2-3
thru 2-12 0 8-1 0
3-1 thru 3-11 0 8-2 Blank 0
3
c12 Blank 0 8-3
thru 8-14 0
3-13
thru 3-21 0
9-1 thr u 9-3 0
3-22 Blank 0 9-4 Blank 0
4-1 thru 4-24 0 Supplements (190
Pages)
0
5-1
0 (Refer to Section 9 Table
5-2 Blank 0 of Contents for Optional
5-3 thru 5-31 0 Systems Supplements)
# Zero in this
column indicates an original page.
A

CESSNA
MODELT210M
CONGRATULATIONS
CONGRATULATIONS • • • •
Welcome to the ranks of Cessna owners! Your Cessna has been designed and
,. ,·- constructed to giveyou the most in performance, economy, and comfort. It is our desirethat
you will find flying it, either for business or pleasure, apleasant and profitable experience.
_._ ,
,-.,,,. ,
This Pilot's Operating Handbook has been prepared as a guide to help you get the most
pleasure and
ut ility from your airplane. It contains information abo ut your Cessna's
equ
ipment , ope rating procedures, and performance; and suggestions for its servicing and
care. We urge you
to read it from cover to cover, and to refer to it frequently.
Our interest in your flying pleasure has not ceased with your purchase of a Cessna.
World-wide, the Cessn a Dealer Organization backed by the Cessna Customer Se rvices
Department stands ready to serve you. The following services are offered by most Cessna
Dealers:
•
THE CESSNA WARRANTY, wh ich provides coverage for parts and labor, is available at
Cessna Dealers
worldwide. Specific benefits and provisions of warranty, plus othe r
import ant benefits for you, are contained in your Customer Care Program book,
supplied with your airplane. Warranty service is available to you at au thorized Cessna
Dealers throughout the world upon presentat ion of your Customer Care Card which
establishes
your eligibility und er the warranty.
•
•
•
•
FACTORY TRAINED PERSO NN EL to provide you with courteous expert service.
FACTORY APPROVED
SERVICE EQUIPMENT to provide you efficient and accurate
workmanship.
A STOCK OF GENUINE
CESSNA SERVICE PARTS on hand when you need them.
THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING CESSNA AIR-
PLANES , since C essna Dealers have all of the-Service Manuals and Parts Catalogs, kept
cur rent by Service Letters and Service News·Letters, published by Cessna Aircraft
Company.
We urge all Cessna owners to use the Cessna Dealer Organization to the fullest.
A
current Cess na Dealer Directory accompanies your new airplane. The Directory is
revised frequently, and a current copy can be obtained from your Cessna Dealer. Make your
Directory one of your cross-country flight planning aid s; a warm welcome awaits you at
every
Cessna Dealer.

PERFORMANCE-
SPECIFICATIONS
CESSNA
MODELT210M
PERFORMANCE - ·SPECIFICATIONS
SPEED:
Maximum at 17,000 Ft
Cruise , 80% Power at 20,000 Ft
Cruise, 80% Power at 10,000 Ft
CRUISE: Recommended lean mixture with fuel allowance for
engine start, taxi, takeoff, climb and 45 minutes
reserve at 45% power .
80% Power at 20,000 Ft
534 Pounds Usable Fuel
80 % Power at 10,000 Ft
534 Pounds Usable Fuel
Maximum Range at 20,000 Ft
534 Pounds Usable Fuel
Maximum Range at 10,000 Ft
534 Pounds Usable Fuel
RATE OF CLIMB AT SEA LEVEL
SERVICE CEILING
TAKEOFF PERFORMANCE:
Ground Roll . . . . . .
Total Distance Over 50-Ft Obstacle
LANDING PERFORMANCE:
Ground Roll . . . . . . . . . . .
Total Distance Over 50-Ft Obstacle
ST ALL SPEED (CAS):
Flaps Up, Power Off
Flaps Down, Power Off
MAXIMUM WEIGHT:
Ramp ....... .
Takeoff and Landing .
STANDARD EMPTY WEIGHT:
Turbo Centurion . . . .
Turbo Centurion II . . .
MAXIMUM USEFUL LOAD:
Turbo Centurion . . . .
Turbo Centurion II . . .
BAGGAGE ALLOWANCE: Maximum With 4 People
WING LOADING: Pounds/ Sq Ft
POWER LOADING : Pounds/HP
FUEL CAP A CITY : Total . . . .
OIL CAPACITY . . . . . . . .
.Range
Time
.Range
Time
.Range
Time
.Range
Time
ENGINE: Teledyne Continental, Turbocharged Fuel Injection
310 BHP at 2700 RPM (5-Minute Takeoff.Rating)
285 BHP at 2600 RPM (Maximum Continuous Rating)
PROPELLER: 3-Bladed Constant Speed , Diameter
ii
. 205 KNOTS
. 198 KNOTS
. 181 KNOTS
830NM
4.4 HRS
790NM
4.5 HRS
995NM
7.1 HRS
990NM
7. 4HRS
1030 FPM
28,500 FT
1150 FT
1900 FT
765 FT
1500 FT
65 KNOTS .
56KNOTS
3816 LBS
3800 LBS
2240 LBS
2306 LBS
1576 LBS
1510 LBS
240 LBS
21.7
12.3
90
GAL.
11 QTS
TSI0-520-R
BOIN.

CESSNA
MODEL T210M
TABLE OF CONTENTS
TABLE OF CONTENTS
SECTION
GENERAL
............................. 1
LIMITATIONS ......................... 2
EMERGENCY PROCEDURES
............ 3
NORMAL PROCEDURES ............... 4
PERFORMANCE
....... .. .. . ..... .... .. 5
WEIGHT & BALANCE/
EQUIPMENT LIST ......... . ....... 6
AIRPLANE &
SYSTEMS
DESCRIPTIONS ................... 7
AIRPLANE
HANDLING,
SERVICE & MAINTENANCE ........ 8
SUPPLEMENTS
(Optional Systems Description
& Operating Procedures) .......... 9
iii/ (iv blank)

CESSNA
MODEL T210M
SECTION 1
GENERAL
TABLE OF CONTENTS
Three View
Introduction
Descriptive Data
Engine
Propeller
Fuel . .
Oil
Maximum Certificated Weights
Standard Airplane Weights
Cabin And Entry Dimensions .
Baggage Space And Entry Dimensions
Specific Loadings . . . . . . . . .
Symbols, Abbreviations And Terminology
General Airspeed Termino l ogy And Symbols
Meteorological Terminology . . . . . . .
Engine Power Terminology . . . . . . . .
SECTION 1
GENERAL
Airplane Performance And Flight Planning Terminology
Page
1-2
1-3
1-3
1-3
1c3
1-3
1-4
1-4
1-4
1-5
1-5
1-5
1-5
1-5
1-6
1-6
1-7
1-7 Weight And Balance Terminology ...... . ... .
1-1

SECTION 1
GENERAL
L-----
PIVOT POINT *
@
4 °7'
CESSNA
MODELT210M
9'-5" MAX .
J
28'-2" _ _..'.... ______ ..,,
NOTES:
1. Max im um height shown with
nose gear depressed, all tire5
and nose strut properly in~
flated and flashing beacon
installed.
2. Wheel base length is 72".
3. Propeller ground clearance is
10 7/8".
4. Wing area is 175 square feet.
5. Minimum turning radius
I* pivot point to outboard
wing tip ) is 26'.
*PIVOT POINT
@
i-+----------------36 '- 9"----------------i
80 " MAX.
Figure 1-1. Three View
1-2

CESSNA
MODELT210M
INTRODUCTION
SECTION 1
GENERAL
This handbook contains 9 sections, and includes the material required
to be furnished to the pilot by CAR Part 3. It also contains supplemental
data supplied by Cessna Aircraft Company.
Section 1 provides basic data and information of general interest. It
also contains defin i tions or exp l anations of symbols, abbreviations, and
terminology commonly used.
DESCRIPTIVE DATA
ENGINE
Number of Engines: 1.
Engine Manufacturer: Te ledyne Continental.
Engine Model Number: TSIO-520-R.
Engine Type: Turbocharged, direct-drive, air-cooled, horizontally-
opposed, fuel-injected, six-cylinder engine with 520 cu . in. displace-
ment.
Horsepower Rating and Engine Speed:
Maximum Power (5 minutes -takeoff): 310 rated BHP at 36.5 inches Hg
and 2700 RPM.
Maximum Con tinuous Power: 285 rated BHP at 35 inches Hg and 2600
RPM.
PROPELLER
Propeller Manufacturer: McCauley Accessory Division .
Propeller Model Number : D3A34C402/90DFA-10.
Number of Blades: 3;
Propeller Diameter, Maximum: 80 inches .
Minimum: 78.5 inches.
Propeller Type : Constant speed and hydraulically actuated , with a low
pitch setting of 12.4° and a high pitch setting of 28.5° (30 inch station) .
FUEL
Approved Fuel Grades (and Colors):
100LL Grade Aviation Fuel (Blue).
100 (Fo rm erly 100/130) Grade Aviation Fuel (Green).
To tal Capacity: 90 gallons.
Total Capacity Each Tank: 45 gallons.
Total Usable: 89 gallons.
1-3

SECTION 1
GENERAL
CESSNA
MODELT210M
OIL
Oil Grade (Specification) :
MIL-L-6082 Aviation Grade Straight Mineral Oil: Use to replenish
supply during first 25 hours and at the first 25-hour oil change.
Continue to use until a total of 50 hours has accumulated or oil
consumption has stabilized.
NOTE
The airplane was delivered from the factory with a corro-
sion preventive aircraft engine oil. This oil should be
drained after the first 25 hours of operation.
Continental Motors Specification MHS-24A , Ashless Dispersant Oil :
This oil must be used after first 50 hours or oil consumption has
stabilized.
Recommended Viscosity for Temperature Range:
SAE 50 above 4°C (40°F).
SAE 10W30 or SAE 30 below 4°C (40°F).
NOTE
Multi-viscosity oil with a: range of SAE 10W30 is recom-
mended for improved starting and turbocharger controlle r
operation in cold weather .
Oil Capacity:
Sump: 10 Quarts.
Total : 11 Quarts (with oil filter).
MAXIMUM CERTIFICATED WEIGHTS
Takeoff : 3800 lbs.
La nding: 3800 lbs.
Weight in Baggage Compartment :
Baggage - Forward of wheel well on folded down aft seat (Station 89 to
110): 120 lbs.
Baggage - On and aft of wheel well (Station 110 to 152): 120 lbs.
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight, Turbo Centurion : 2240 lbs.
Turbo Centurion II: 2306 lbs.
Maximum Useful Load , Turbo Centurion: 1576 lbs .
Turbo Centurion II: 1510 lbs.
1-4

, ..-,...., ,.,
CESSNA
MODEL T210M
SECTION 1
GENERAL
CABIN AND ENTRY DIMENSIONS
Detailed dimensions of the cabin interior and entry door openings are
illustrated in Section 6.
BAGGAGE SPACE AND ENTRY DIMENSIONS
Dimensions of the baggage area and baggage door opening are
illustrated in detail in Section 6.
SPECIFIC LOADINGS
Wing Loading: 21.7 lbs,/sq. ft.
Power Loading: 12.3 lbs./hp.
SYMBOLS, ABBREVIATIONS AND
TERMINOLOGY
GENERAL AIRSPEED T ERMINOLOGY AND SYMBOLS
KCAS
KIAS
KTAS
VA
VFE
VLE
VLO
Knots Calibrated Airspeed is indicated airspeed corrected
for position and instrument error and expressed in knots.
Knots calibrated airspeed is equal to KT AS in standard
atmosphere at sea level.
Knots Indicated Airspeed is the speed shown on the
airspeed indicator and expressed in knots.
Knots True Airspeed is the airspeed expressed in knots
relative to undisturb ed air which is KCAS corrected for
altitude and temperature .
Manuevering Speed is the maximum speed at which you
may use abrupt control travel.
Maximum Flap Extended Speed is the highest speed
permissible with wing flaps in a prescribed extended
position.
Maximum Landing Gear Extended Speed is the maximum
speed at which an airplane can be safely flown with the
landing gear extended.
Maximum Landing Gear Operating Speed is the maximum
speed at which the landing gear can be safely extended or
retracted.
1-5

SECTION 1
GENERAL
VNE
CESSNA
MODEL T210M
Maximum Structural Cruising Speed is the speed that
should not be exceeded except in smooth air, then only with
caution.
Never Exceed Speed is the speed limit that may not be
exceeded at any time.
Stalling Speed or the mm1mum steady flight speed at
which the airplane is controllable.
Stalling Speed or the minimum steady flight speed at
which the airplane is controllable in the landing configu-
ration at the most forward center of gravity.
Best Angle-of-Climb Speed is the speed which results in
the greatest gain of altitude in a given horizontal .distance.
Best Rate-of-Climb Speed is the speed which results in the
greatest gain in altitude in a given time.
METEOROLOGICAL TERMINOLOGY
OAT
Standard
Tempera-
ture
Pressure
Altitude
Outside Air Temperature is the free air static temperature.
It is expressed in either degrees Celsius (formerly Centi-
grade) or degrees Fahrenheit .
Standard Temperature is 15°C at sea level pressure alti-
tude and decreases by 2°C for each 1000 feet of altitude.
Pressure Altitude is the altitude read from an altimeter
when the altimeter's barometric scale has been set to 29.92
inches of mercury (1013 mb).
ENGINE POWER TERMINOLOGY
RPM
MP
1-6
Brake Horsepower is the power developed by the engine.
Percent power values in this handbook are based on the
maximum continuous power rating.
Revolutions Per Minute is engine speed.
Manifold Pressure is a pressure measured in the engine's
induction system and is expressed in inches of mercury
(Hg).

,---.___
,,........,,_,
CESSNA
MODELT210M
SECTION 1
GENERAL
AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
Demon-
strated
Crosswind
Velocity
Usable Fuel
Unusable
Fuel
PPH
NMPG
g
Demonstrated Crosswind Velocity is the velocity of the
crosswind component for which adequate control of the
airplane during takeoff and landing was actually demon-
strated during certification tests . The value shown is not
considered to be limiting .
Usable Fuel is the fuel available for flight planning.
Unusable Fuel is the quantity of fuel that can not be safely
used in flight.
Pounds Per Hour is the amount' of fuel (in pounds) con -
sumed per hour.
Nautical Miles Per Gallon is the distance (in nautical
miles) which can be expected per gallon of fuel consumed
at a specific engine power setting and/ or flight configura-
tion.
g is acceleration due to gravity.
.--..., WEIGHT AND BALANCE TERMINOLOGY
Reference
Datum
Station
Arm
Moment
Center of
Gravity
(C.G.)
Refer ence Datum is an imaginary vertical plane from
which all horizontal distances are measured for balance
purposes.
Station is a location along the airplane fuselage given in
terms of the distance from the reference datum.
Arm is the horizontal distance from the reference datum to
the center of gravity (C.G.) of an item.
Moment is the product of the weight of an item multiplied
by its arm. (Moment divided by the constant 1000 is used in
this ha ndbook to simplify balance calculations by reduc -
ing the number of digits.)
Center of Gravity is the point at whi ch an airplane, or
equi pment, would balance if suspended. Its distance from
the reference datum is found by dividing the total moment
by the total weight of the airplane .
1-7

SECTION 1
GENERAL
C.G.
Arm
C.G.
Limits
Standard
Empty
Weight
Basic Empty
, . Weight
Useful
Load
Maximum
Ramp
Weight
Gross
(Loaded)
Weight
Maximum
Takeoff
Weight
Maximum
Landing
Weight
Tare
1-8
CESSNA
MODELT210M
Center of Gravity Arm is the arm obtained by adding the
airplane's individual moments and dividing the sum by
the total weight.
Center of Gravity Limits are the extreme center of gravity
locations within which the airplane must be operated at a
given weight.
Standard Empty Weight is the weight of a standard air-
plane, including unusable fuel, full operating fluids and
full engine oil.
Basic Empty Weight is the standard empty weight plus the
weight of optional equipment.
Useful Load is the difference between ramp weight and the
basic empty weight.
Maximum Ramp Weight is the maximum weight approved
for ground maneuver. (It includes the weight of start, taxi
and runup fuel.)
Gross (Loaded) Weight is the loaded weight of the airplane.
Maximum Takeoff Weight is the maximum weight
approved for the start of the takeoff run.
Maximum Landing Weight is the maximum weight
approved for the landing touchdown.
Tare is the weight of chocks, blocks, stands, etc. used when
weighing an airplane, and is included in the scale read-
ings . Tare is deducted from the scale reading to obtain the
actual (net) airplane weight.

~
CESSNA
MODELT210M
SECTION 2
LIMITATIONS
TABLE OF CONTENTS
Introduction . . . . . . . .
Airspeed Limitations
Airspeed Indicator Markings
Power Plant Limitations
Power Plant Instrument Markings
Weight Limits . . . . . .
Center Of Gravity Limits .
Maneuver Limits
Flight Load Factor Limits
Kinds Of Operation Limits
Fuel Limitations
Placards . .. . ... .
SECTION 2
LIMITATIONS
Page
2-3
2-4
2-4
2-5
2-6
2-7
2-7
2-7
2-7
2-7
2-8
2-9
2-1/(2-2 blank)

CESSNA
MODELT210M
SECTION 2
LIMITATIONS
INTRODUCTION
Section 2 includes operating limitations, instrument markings, and
basic placards necessary for the safe operation of the airplane; its engine,
standard systems and standard equipment. The limitations included in
this section have been approved by the Federal Aviation Administration.
When applicable, limitations associated with optional systems or equip-
ment are included in Section 9.
NOTE
The airspeeds listed in the Airspeed Limitations chart
(figure 2-1) and the Airspeed Indicator Markings chart
(figure 2-2) are based on Airspeed Calibration data shown
in Section 5 with the normal static source . If the alternate
static source is being used, ample margins should be
observed to allow for the airspeed calibration variations
between the normal and alternate static sources as shown
in Section 5.
Your Cessna is certificated under FAA Type Certificate No. 3A21 as
Cessna Model No. T210M.
2-3

SECTION 2
LIMIT A TIO NS
AIRSPEED LIMITATIONS
CESSNA
MODELT210M
Airspeed limitations and their operational significance are shown in
figure 2-1.
SPEED
KCAS
KIAS
REMARKS
VNE Never Exceed
Speed
195 195 Do not exceed this speed in
any operation.
VNO Maximum Structural 165 165 Do
not exceed this speed
Cruising Speed except in smooth air, and
then
only with caution.
VA
Maneuvering Speed:
3800 Pounds 118 119 Do
not make full or abrupt
3200 Pounds 109 110 control movements above
2600 Pounds 97 : 98 this
speed .
VFE Maximum Flap Extended
Speed :
To 10° Flaps 149 150 Do
not exceed these speeds
10° - 30° Flaps 114 115
with the given flap settings.
VLO
Maximum Landing Gear 139 140 Do
not extend or retract
Operating
Speed
landing gear above this
speed.
VLE
Maximum Landing Gear
195 195 Do not exceed this speed
Extended Speed
with landing gear extended.
Maximum Window Open 195
195
Do not exceed this speed with
Speed
windows open.
Figure 2-1. Airspeed Limitations
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code significance are
shown in figure 2-2.
2-4

~
~
CESSNA
MODELT210M
SECTION2
LIMITATIONS
MARKING
KIAS VALUE
SIGNIFICANCE
OR RANGE
White Arc
55-115
Full Flap Operating Range. Lower limit is
' maximum weight
Vs
0 in landing configu-
ration. Upper
limit is maximum speed per-
missible
with flaps extended.
Green Arc 68 -165
Normal Operating Range.
Lower limit is
maximum weight Vs at most forward C.G.
with flaps retracted. Upper
limit is maxi-
mum structural cruising
speed .
Yellow Arc 165 -195 Operations must
be conducted with
caution and only in smooth air.
Red Line 195 Maximum speed for all operations.
Figure 2-2. Airspeed Indicator Markings
POWER PLANT LIMITATIONS
Engine Manufacturer : Teledyne Continental.
Engine Model Number: TSIO-520-R.
Engine Operating Limits for Takeoff and Continuous Operations:
Maximum Power, 5 Minutes - Takeoff: 310 BHP.
Continuous: 285 BHP
Maximum Engine Speed, 5 Minutes - Takeoff: 2700 RPM.
Continuous: 2600 RPM.
Maximum Manifold Pressure, 5 Minutes - Takeoff: 36.5 inches Hg.
Continuous: 35 inches Hg.
NOTE
For manifold pressure limitations above 17,000 feet, refer
to the Maximum Power Setting and Fuel Flow placard in
this section.
Maximum Cylinder Head Temperature: 238°C (460°F).
Maximum Oil Temperature: 116°C (240°F).
Oil Pressure, Minimum: 10 psi.
Maximum: 100 psi.
Fuel Pressure, Minimum: 3.0 psi.
Maximum: 19.5 psi (186 lbs/hr).
2-5

SECTION 2
LIMITATIONS
CESSNA
MODELT210M
Propeller Manufacturer: McCauley Accessory Division.
Propeller Model Number: D3A34C402/90DFA-10 .
Propeller Diameter, Maximum: 80 inches.
Minimum: 78.5 inches.
Propeller Blade Angle at 30 Inch Station , Low : 12.4°.
High: 28.5°.
Propeller Operating Limits: Avoid continuous operation between 1850
and 2150 RPM above 24 inches manifold pressure .
POWER PLANT INSTRUMENT MARKINGS
Power plant instrument markings and their color code significance
are shown in figure 2-3.
RED LINE GREEN ARC YELLOW ARC WHITE ARC RED LINE
INSTRUMENT
MINIMUM NORMAL
CAUTION
NORMAL
MAXIMUM
LIMIT OPERATING RANGE CLIMB
LIMIT
RANGE
Tachometer - - -2200 -2600 ----2700
RPM
2500 RPM
2700 RPM
Manifold Pressure -- - 15 -30 35 -36.5 - - - 36.5 in.
Hg
in. Hg
in. Hg
Oil Temperature ---
100° -240°F - - - - - - 240°F
Cylinder
Head -- - 200° -
460°F
--- ---
460°F
Temperature
Fuel Flow (3.0 psi) 36 -120 - - - 120 -162 186 lbs/hr
(Pressure)
lbs/hr lbs/hr (19.5 psi)
Oil
Pressure
10 psi
30 -60 psi
- - - -- - 100
psi
Figure 2-3. Power Plant Instrument Markings
2-6