Cessna 182S Skylane Quick setup guide

Textr
182S Skylane
182StM

NOTICE
AT THE TIME OF ISSUANCE, THIS
INFORMATION MANUAL WAS AN EXACT
DUPLICATE OF THE OFFICIAL PILOT'S
OPERATING HANDBOOK AND FAA
APPROVED AIRPLANE FLIGHT MANUAL
AND IS TO BE USED FOR GENERAL
PURPOSES ONLY.
IT WILL NOT BE KEPT CURRENT AND,
THEREFORE, CANNOT BE USED AS A
SUBSTITUTE FOR THE OFFICIAL PILOT'S
OPERATING HANDBOOK AND FAA
APPROVED AIRPLANE FLIGHT MANUAL
INTENDED FOR OPERAT¡ON OF THE
AIRPLANE.
CESSNA AIRCRAFT COMPANY
OR¡GINAL ISSUE .3 FEBRUARY 1997
FebS/97

PERFORMANCE.
SPECIFICATIONS CESSNA
MODEL 182S
PERFORMANCE - SPECIFICATIONS
* SPEED
Maximum at Sea Level 145 KTS
Cruise, 80% Power at 6000 Ft (Best Power Mixture) 140 KTS
CRUISE: Recommended lean mixture with fuel allowance for
engine start, taxi, takeoff, climb and 45 minutes
reserue.
71"/oPower at 6000 Ft Range 820 NM
88 Gallons Usable Fuel Time 6'05 HRS
Max Range at 10,000 Fl,55o/o Power Range 968 NM
88 Gallons Usable Fuel Time 8.05 HRS
RATE OF CLIMB AT SEA LEVEL: 924 FPM
SERVICE CEILING: 18,100 FT
TAKEOFF PERFORMANCE:
Ground Roll 795 FT
Total Distance Over 50 Ft. Obstacle 1514 FT
LANDING PERFORMANCE:
Ground Roll 590 FT
Total Distance Over 50 Ft. Obstacle 1350 FT
STALL SPEED (KCAS):
Flaps Up, Power Otf 54 KCAS
Flaps Down, Power Off . . 4s KCAS
MAXIMUM WEIGHT:
Ramp 3110 LBS
31OO LBS
2950 LBS
1 925 LBS
1 185 LBS
2OO LBS
Takeotf
Landing
STANDARD EMPTY WEIGHT:
MAXIMUM USEFUL LOAD:
BAGGAGE ALLOWANCE:
Nov 15/00

WING LOADING: Lbs/Sq Ft
POWER LOADING Lbs/HP
PER FOR MAN C E.SPECI FICATIONS
(Continued)
17.8
FUEL CAPACITY
OIL CAPACITY
CESSNA
MODEL 182S PERFORMANCE-
SPECIFICATIONS
13.5
92 GAL
9 QTS
ENGINE: Textron Lycoming |O-540-AB1A5
230 BHP at 2400 RPM
PROPELLER: Diameter - 3-Blade
Diameter - 2-Blade í; iill
NOTE
*Speed performance and range are shown for an airplane
equipped with optional speed fairings which increase the
speeds by approximately 3 knots. All other performance
when speed fairings are removed.
based on a 2-bladed propeller. I
3-blade propeller is essentially the I
The above performance figures are based on the indicated
weights, standard atmospheric conditions, level hard'surface
dry runways and no wind. They are calculated values derived
from flight tests conducted by the Gessna Aircraft Company
under carefully documented conditions and will vary with
individual airplanes and numerous other factors affecting flight
performance.
Dec 1/97 iii/(iv blank)

lnformation Manual
COPYRIGHT@ 1997
The Cessna Aircraft Company
Wichita, Kansas USA
Nov 1/01
Cessna Aircraft Company
Model 182S
THIS MANUAL INCORPORATES INFORMATION ISSUED
THRU REVISION 04 TO THE PILOTS OPERATING
HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT
MANUAL DATED 3 FEBRUARY 1997.
Q uenaerofGAMA
P/N: 182SlM
v/(viblank)

CESSNA
MODEL 182S TABLE OF CONTENTS
SECTION
TABLE OF CONTENTS
GENERAL
LIMITATIONS
EMERGENCY PROCEDURES
NORMAL PROCEDURES
PERFORMANCE
WEIGHT & BALANCE/EQUIPMENT LIST
A¡RPLANE & SYSTEMS DESCRIPTION
HANDLING, SERVICE & MAINTENANCE
SUPPLEMENTS
1
2
3
4
5
6
7
I
I
Feb 3/97 vii/(viiiblank)

CESSNA
MODEL 182S SECTION 1
GENERAL
SECTION 1
GENERAL
TABLE OF CONTENTS
Three View - Normal Ground Attitude
lntroduction
Descriptive Data
Engine
Propeller (2-Bladed)
Page
Propeller (3-Bladed)
Fuel
oit
Maximum Cefi if icated Weights
Standard Airplane Wei ghts
Cabin And Entry Dimensions
Baggage Space and Entry Dimensions
Specific Loadings 1-7
Symbols, Abbreviations and Terminology 1-8
GeneralAirspeed Terminology And Symbols . . . 1-8
MeteorologicalTerminology 1-9
Engine Power Terminology 1-9
Airplane Performance And Flight Planning Terminology 1-10
Weight And Balance Terminology . . . 1-11
Metric / lmperial/ U.S. Conversion Charts 1-13
1-2
1-4
1-4
1-4
1-4
1-4
1-5
1-6
1-7
iit
1-7
Weight Conversions
Length Conversions
Distance Conversions
Volume Conversions
Temperature Conversions
Volume to Weight Conversions
Quick Conversions
1-14
1-16
1-20
1-21
1-24
1-25
1-26
1-1
Nov 15/00

SECTION 1
GENERAL CESSNA
MODEL 182S
0785T1 001
0785T1 001
Figure 1-1. Three View - Normal Ground Attitude (Sheet 1 ol2)
1-2 Feb 3/97

CESSNA
MODEL 182S
NOTE 3:
NOTE 4:
NOTE 5:
NOTE 6:
SECTION 1
GENERAL
NOTE 1: WING SPAN SHOWN WITH STANDARD STROBE
LIGHTS INSTALLED.
NOTE 2: NORMAL GROUND ATTITUDE IS SHOWN WITH
NOSE STRUT SHOWING APPROXIMATELY 2" OF
STRUT, AND WINGS LEVEL.
WHEEL BASE LENGTH lS 661/z'.
PROPELLER GROUND CLEARANCE IS 1O ".
WING AREA IS 174 SQUARE FEET.
MtNtMUM TURNTNG RADTUS (.ptVOT potNT TO
oUTBoARD W|NG TtP) tS 27', - 0".
0785T1001
Figure 1-1. Three View - Normal Ground Attitude (Sheet 2 of 2)
Feb 3197 1-3

SECTION 1
GENERAL CESSNA
MODEL 182S
INTRODUCTION
This handbook contains 9 sections, and includes the material
required to be furnished to the pilot by FAR Part 23' lt also contains
supplemental data supplied by The Cessna Aircraft Company.
Section 1 provides basic data and information of general interest'
It also contains definitions or explanations of symbols,
abbreviations, and terminology commonly used.
DESCRIPTIVE DATA
ENGINE
Number of Engines: 1.
Engine Manufacturer: Textron Lycoming.
Engine Model Number: lO-540-AB1 45.
Engine Type: Normally aspirated, direct drive, air-cooled,
- horizontally opposed, fuel injected, six cylinder engine with
541 cu. in. displacement.
Horsepower Rating and Engine Speed: 230 rated BHP
at 2400 RPM.
PROPELLER (2-Bladed)
Propeller Manufacturer: Mc0auley Propeller Systems.
Propeller Model N umber: B.2D34C235/90DKB-8'
Number of Blades: 2.
Propeller Diameter: 82 inches.
Propeller Type: Constant speed and hydraulically actuated, wlth .a
low'pitch sétting of 17.0' and a high pitch setting of 31.8' (30 inch
station).
PROPELLER (3-Bladed)
Propeller Manufacturer: McOauley Propeller Systems.
Propeller Model Number: 83D36C431/80VSA-1.
Number of Blades: 3.
Propeller Diameter: 79.0 inches.
Propeller Type: Constant speed and hydraulically actuated, wlth.a
low pitch sétting of 14.9' and a high pitch setting of 31.7' (30 inch
station).
1-4 Dec 1197

CESSNA
MODEL 182S SECTION 1
GENERAL
FUEL
¡[, wnnrrruo
USE OF UNAPPROVED FUELS MAY RESULT IN
DAMAGE TO THE ENGINE AND FUEL SYSTEM
COMPONENTS, RESULTING IN POSSIBLE
ENGINE FAILURE.
Approved FuelGrades (and Colors):
100LL Grade Aviation Fuel (Blue).
100 Grade Aviation Fuel (Green).
NOTE
lsopropyl alcohol or diethylene glycol monomethyl ether
(DiEGME) may be added to the fuel supply. Additive
concentrations shall not exceed 17" lor isopropyl alcohol or
0.10% to 0.15% for D|EGME. Refer to Section I for
additional information.
FuelCapacity:
TotalCapacity: 92.0 U.S. gallons.
Total Usable: 88.0 U.S. gallons.
Total Capacity Each Tank: 46.0 U.S. gallons.
Total Usable Each Tank: 44.0 U.S. gallons.
NOTE
To ensure maximum fuel capacity and minimize cross-
feeding when refueling, always park the airplane in a wings-
level, normal ground attitude and place the fuel selector in
the Left or Right position. Refer to Figure 1-1 for normal
ground attitude dimensions.
1-5
Nov 15/00

SECTION 1
GENERAL
olL
CESSNA
MODEL 182S
Oil Specification:
MiL-L-6082 Aviation Grade Straight Mineral Oil: Used when the
airplane was delivered from the factory and should be used to
replenish the supply during the first 25 hours. This oil should be
drained and the filter changed after the first 25 hours of operation.
Refill the engine with MIL-L-6082 Aviation Grade Straight Mineral
Oil and contiñue to use until a total of 50 hours has accumulated or
oil consumption has stabilized.
MIL-L-22851 Aviation Grade Ashless Dispersant Oil: Oil
conforming to Textron Lycoming Seruice lnstruction No 1014' and
all revisioñs and supplements thereto, must be used after first 50
hours or once oil consumption has stabilized.
Recommended Viscosity for Temperature Range:
Temperature MtL-L-6082
SAE Grade MIL-L-22851
Ashless Dispersant
SAE Grade
{bove 27'C (80'F) 60 60
\bove 16"C (60"F) 50 40 or 50
1 "C (30'F) to 32"C (90'F) 40 40
-18'C (0"F) to 21'C (70"F) 30 30. 40 or 20W-40
3elow -12"C (10'F) 20 30 or 20W-30
-18'C (0"F) - 32'C (90'F) 20w-50 20W-50 or 15W-50
All Temoeratures 15W-50 or 2OW-50
NOTE
When operating temperatures overlap, use the lighter grade
of oil.
OilCapacity:
Sump: I U.S. Quarts
Total: I U.S. Quarts
1-6 Nov 15/00

CESSNA
MODEL 182S SECTION 1
GENERAL
MAXIMUM CERTIFICATED WEIGHTS
Ramp Weight : 3110 lbs.
Takeoff Weight: 3100 lbs.
Landing Weight : 2950 lbs.
Weight in Baggage Compadment, NormalCategory:
Baggage Area A (Station 82 to 109): 120 lbs. See note below.
Baggage Area B (Station 109 to 124): 80 lbs. See note below.
Baggage Area C (Station 1241o 134): 80 lbs. See note below.
NOTE
The maximum allowable combined weight capacity for
baggage in areas A, B and C is 200 pounds. The maximum
allowable weight capacity for baggage in areas B and C is 80
pounds.
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight: 1925 lbs. I
Maximum Useful Load, Normal Category: 1185 lbs. I
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: 17.8|bs./sq. ft.
Power Loading: 13.5 lbs./hp.
.- j
Nov 15/00 1-7

SECTION 1
GENERAL
KIAS
KTAS
V¡
Vre
vruo
vrue
Vs
Vso
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
Knots Calibrated Airspeed is indicated airspeed
corrected for position and instrument error and
expressed in knots. Knots calibrated airspeed is equal
to KTAS in standard atmosphere at sea level.
Knots lndicated Airspeed is the speed shown on the
airspeed indicator and expressed in knots.
Knots True Airspeed is the airspeed expressed in
knots relative to undisturbed air which is KCAS
corrected for altitude and temperature.
Maneuvering Speed is the maximum speed at
which full or abrupt control movements may be used.
Maximum Flap Extended Speed is the highest
speed permissible with wing flaps in a prescribed
extended position.
Maximum Structural Cruising Speed is the speed
that should not be exceeded except in smooth air,
then only with caution.
Never Exceed Speed is lhe speed limit that may not
be exceeded at any time.
Stalling Speed or the minimum steady flight
speed is the minimum speed at which the airplane is
controllable.
Stalling Speed or the minimum steady flight
speed is the minimum speed at which the airplane is
controllable in the landing configuration at lhe most
forward center of gravity.
CESSNA
MODEL 182S
1-8 Feb 3197

CESSNA
MODEL 182S
V¡
SECTION 1
GENERAL
Best Anql+of-Climb Soeed is the soeed which re-
sults in tñe greatest gain of altitude ih a given hori-
zontaldistanðe.
Vy Best Rate-of-Glimb Speed is the speed which
results in the greatest gain in altitude in a given time.
METEOROLOGICAL TERMINOLOGY
OAT Outside Air Temperature is the free air static
temperature. lt may be expressed in either degrees
Celsius or degrees Fahrenheit.
Standard Standard Temperature is 15'C at sea level
Temperature pressure altitude and decreases by 2"C for each
1000 feet of altitude.
Pressure Pressure Altitude is the altitude read from an
Altitude altimeter when the altimeter's barometric scale has
been set lo 29.92 inches of mercury (1013 mb).
ENGINE POWER TERMINOLOGY
BHP Brake Horsepower is the power developed by the
engine.
RPM Revolutions Per Minute is engine speed.
Static Static RPM is engine speed attained during a full
RPM throttle engíne runup when the airplane is on the
ground and stationary.
MP Manifold Pressure is a pressure measured in the
engine's induction system and is expressed in
inches of mercury (in Hg).
-.-:
Feb 3/97 1-9

SECTION 1
GENERAL CESSNA
MODEL 182S
AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
Demon- Demonstrated Crosswind Velocity is the velocity
strated of the crosswind component for which adequate
Crosswind control of the airplane during takeoff and landing
Velocity was actually demonstrated during certification tests.
- The value shown is not considered to be limiting.
Usable Fuel Usable Fuel is the fuel available for flight planning'
Unusable Unusable Fuel is the quantity of fuel that can not be
Fuel safely used in flight.
GPH Gallons Per Hour is the amount of fuel consumed
oer hour.
NMPG Nautical Miles Per Gallon is the distance which can
be expected per gallon of fuel consumed at a
specif ió engine power setting and/or f light
configuration.
g g is acceleration due to gravitY'
Course Course Datum is the compass reference used by the
Datum autopilot, along with course deviation, to provide
lateral controlwhen tracking a navigation signal.
1-10 Feb 3197

CESSNA
MODEL 182S
c.G.
Arm
c.G.
Limits
SECTION 1
GENERAL
WEIGHT AND BALANCE TERMINOLOGY
Reference Reference Datum is an imaginary vertical plane from
Datum which all horizontal distances are measured for
balance purposes.
Station Station is a location along the airplane fuselage given
in terms of the distance from the reference datum.
Arm Arm is the horizontal distance from the reference
datum to the center of gravity (C.G.) of an item.
Moment Moment is the product of the weight of an item
multiplied by its arm. (Moment divided by the conslant
1000 is used in this handbook to simplify balance
calculations by reducing the number of digits.)
Center of Center of Gravity is the point at which an airplane, or
Gravity equipment, would balance if suspended. lts distance
(C.G.) from the reference datum is found by dividing the
total moment by the total weight of the airplane.
Center of Gravity Arm is the arm obtained by
adding the airplane's individual moments and dividing
the sum by the totalweight.
Center of Gravity Limits are the extreme center of
gravity locations within which the airplane must be
operated at a given weight.
Standard Standard Empty Weight is the weight of a standard
Empty airplane, including unusable fuel, full operating fluids
Weight and full engine oil.
Basic Empty Basic Empty Weight is the standard empty weight
Weight plus the weight of optional equipment.
Useful Load Useful Load is the difference between ramp weight
and the basic empty weight.
MAC MAC (Mean Aerodynamic Chord) is a chord of an
imaginary rectangular airfoil having the same pitching
moments throughout the flight range as that of the
actualwing.
Feb 3197 1-11