Cessna 182 1973 User manual

(EssnA
MORE PEOPLE BUY AND
FLY CESSNA AIRPLANES
THAN ANY OTHER MAKE
1973
WORLD'S LARGEST PRO-
DUCER OF GENERAL
AVIATION AIRCRAFT
SINCE 1956
MODEL
185=
A. ITN ID
SKYLANE
—
OWNERS
MANUAL

PERFORMANCE -SPECIFICATIONS
GROSS WEIGHT .......«oo vo ov on
SPEED:
Top Speed at Sea Level .. . . ... . . ...
Cruise, 75% Power at 65001 .........
RANGE:
Cruise, 75% Power at 6500 ft .........
60 Gallons, No Reserve
Cruise, 75% Power at 6500 ft .........
79 Gallons, No Reserve
Optimum Range at 10,000 ft. .......
§0 Gallons, No Reserve
Optimum Range at 10,000 ft. ..... . . .
79 Gallons, No Reserve
RATE OF CLIMB AT SEA LEVEL
SERVICE CEIDING
|
i¢oo &5
+% = ing 4#4 on ©
TAKE-OFF:
Ground Run. .“ee a
Total Distance Over 50- Foot Obstacle ow
LANDING:
Ground Roll ...
.....
+«oo ooo
Total Distance Over '50-Foot Obstacle . . .
STALL SPEEDS:
Flaps Up, Power Off ......... . ....
Flaps Down, Power Off .. . . . ....
EMPTY WEIGHT: (Approximate)
Skylane .....NAN NE Bw mk
REST SN Po a
USEFUL LOAD:
Skylane . .....aacs Ed
MOdeU BE i. v5 wm ews mee ai Sie
BAGGAGE:
Forward Area "A" (Station 82 to 108) ......
Aft Area "B" (Station 108 to 124) . . .... . .
WING LOADING: Pounds/Sq Foot .....a a 08
POWER LOADING: Pounds/HP . ....:
FUEL CAPACITY: Total
Standard Tanks .. . ««+ +. o«o ww
Optional Long Range Tanks ....
OIL CAPACITY: Total ..
PROPELLER: Constant Speed (Diameter) Ee
ENGINE: Continental Engine vw mow § EEE
230 rated BHP at 2600 RPM
NOTE: Performance data is shown for the Skylane which is 2to 3mph faster
than astandard-equipped Model 182 (without speed fairings).
is acorresponding difference in range, while all other performance
figures are the same for the 182 as shown for the Skylane.
There
Skylane *
2950 lbs
168 mph
160 mph
690 mi
4.3 hrs
160 mph
910 mi
5.7 hrs
160 mph
885 mi
7.7 hrs
115 mph
1160 mi
10.1 hrs
115 mph
890 fpm
17,700 ft
705 ft
1350 ft
590 ft
1350 ft
64 mph
57 mph
1645 lbs
1595 lbs
1305 lbs
1355 Ibs
120 lbs
80 lbs
16.9
12.8
65 gal.
84 gal.
12 gts
82 inches
0-470-R
#This manual covers operation of the Model 182/Skylane which is certificated
as Model 182P under FAA Type Certificate No. 3A13.
D1003-13—RAND-2000-8/73

REVISED
FUELQUANTITY
DATA
LMOD182 Fuses and Circuit Breakers, 2-6 crosswind, 2-17
1973 AIRCRAFT (SERIAL 18262251 AND ON) distance table 6-9
1974 AIRCRAFT (ALL SERIALS) '
SKYLANE 1975 AIRCRAFT (ALL SERIALS) forced, 3-1
Gnormai, 1-7, 2-17
precautionary with power, 3-2
Graph, Loading, 4-7 short field, 2-17
Due to changes in fuel tank manufacturing technique, the fuel systems in the above noted airplanes Gross Weight, inside front cover Landing Gear Servicing, inside
have been found to contain less than the capacity published in the Owner's Manuals. Data in these Ground Handling, 5-1 back cover
manuals indicates total usable capacities of 60 gallons for standard tanks and 79 gallons for long range Ground Service Plug Receptacle, main/nose wheel tire pressure,
tanks; the usable capacity per tank is shown to be 31 gallons and 39 gallons respectivelY· 7-1 inside back cover
All fuel capacity references in Owner'sManuals for these airplanes should be marked to reflect the nose gear shock strut servicing,
capacities in the chart below. inside back cover
HLet-Down, 1-6
Lighting Equipment, 2-6
TOTAL USABLE TOTAL USABLE Handling, Ground, 5-1 exterior lighting, 2-6
BOTHTANKS BOTH TANKS PER TANK PER TANK
CAPACITY Harnesses, Shoulder, 2-9, 2-10 interior lighting, 2-7
(STANDARD TANKS) 61 Gal. 56 Gal. 30.5 Gal. 29 Gal. Headset-Microphone, 7-5 Limitations, Airspeed, 4-2
CAPACITY Heating, Ventilating and Defrosting Limitations, Engine Operation,
(LONG RANGETANKS) 80 Gal. 75 Gal. 40 Gal. 37 Gal. System, Cabin, 2-8 4-2
Hot Weather Operation, 2-21 Loading Arrangements Diagram, 4-5
Loading Graph, 4-7
When figuring weight and balance data, consideration should be given to the reduction in weight Loading Problem, Sample, 4-6
and change in moment/1000 which results from areduced fuel capacity. Long Range Fuel Tanks, 2-3
For quick re-computation of cruise performance data, use the information in the Cruise Performance Low Oil Pressure, 3-8
charts provided in the Owner'sManuals by multiplying the ENOR. HOURSand RANGE MILES figures Indicator, Fuel Quantity, 4-3
by 0.93 (for standard tank values) or 0.94 (for long range tank values); this will provide conservative Indicator, True Airspeed, 7-10
endurance and range based on the reduced fuel capacities. Inspection Requirements, 5-6 M
Pages in the Owner'sManuals which are affected by the change in fuel capacity are listed in the Instrument Markings, Engine,
chart below. 4-2 MAA Plate/Finish Trim Plate, 5-4
Instrument Panel Diagram, 1-8 Magneto Malfunction, 3-8
Insufficient Rate of Electrical Maneuvers -Normal Category, 4-1
MANUAL PAGES AFFECTED Charge, 3-9 Manifold Pressure Gage, 4-3
1973 Integrated Seat Belt/Shoulder Har- Markings, Airspeed Indicator, 4-2
OWNER'S Inside 2-1 2-2 2-14 4-6 4-7 5-8 64 6-5 6-6 6-7 6-8 7-1 Inside nesses With Inertia Reels, 2-10 Markings, Engine Instrument, 4-2
MANUAL Cover Cover Interior Care, 5-4 Master Switch, 2-3
Interior Lighting, 2-7 Maximum Glide Diagram, 6-10
OWNER'S Inside 2-1 22 2-3 2-14 4-6 4-7 6-4 6-5 6-6 6-7 6-8 Inside _Maximum Performance Climb, 1-6
MANUAL Cover Cover Maximum Performance Take-Off,
1975 L1-5
OWNER'S Inside 2-1 22 2-3 4-6 47 6-4 6-5 6-6 6-7 6-8 Inside - - Maximum Rate-Of-Climb Data
MANUAL Cover Cover Landing, 2-17 Chart, 6-3
after, 1-7 Microphone-Headset, 7-5
balked, 1-6, 2-17 Moment Envelope, Center of
THIS ADHESIVE BACKED STICKER IS TO BE ATTACHED TO ANY before, 1-6 Gravity, 4-8
BLANK PAGE IN YOUR MANUAL FOR FUTURE REFERENCE.
REFERENCE SERVICE LETTER SE 75 -7Index-3
REVISED
FUELQUANTITY
DATA
LMOD182 Fuses and Circuit Breakers, 2-6 crosswind, 2-17
1973 AIRCRAFT (SERIAL 18262251 AND ON) distance table 6-9
1974 AIRCRAFT (ALL SERIALS) '
SKYLANE 1975 AIRCRAFT (ALL SERIALS) forced, 3-1
Gnormai, 1-7, 2-17
precautionary with power, 3-2
Graph, Loading, 4-7 short field, 2-17
Due to changes in fuel tank manufacturing technique, the fuel systems in the above noted airplanes Gross Weight, inside front cover Landing Gear Servicing, inside
have been found to contain less than the capacity published in the Owner's Manuals. Data in these Ground Handling, 5-1 back cover
manuals indicates total usable capacities of 60 gallons for standard tanks and 79 gallons for long range Ground Service Plug Receptacle, main/nose wheel tire pressure,
tanks; the usable capacity per tank is shown to be 31 gallons and 39 gallons respectivelY· 7-1 inside back cover
All fuel capacity references in Owner'sManuals for these airplanes should be marked to reflect the nose gear shock strut servicing,
capacities in the chart below. inside back cover
HLet-Down, 1-6
Lighting Equipment, 2-6
TOTAL USABLE TOTAL USABLE Handling, Ground, 5-1 exterior lighting, 2-6
BOTHTANKS BOTH TANKS PER TANK PER TANK
CAPACITY Harnesses, Shoulder, 2-9, 2-10 interior lighting, 2-7
(STANDARD TANKS) 61 Gal. 56 Gal. 30.5 Gal. 29 Gal. Headset-Microphone, 7-5 Limitations, Airspeed, 4-2
CAPACITY Heating, Ventilating and Defrosting Limitations, Engine Operation,
(LONG RANGETANKS) 80 Gal. 75 Gal. 40 Gal. 37 Gal. System, Cabin, 2-8 4-2
Hot Weather Operation, 2-21 Loading Arrangements Diagram, 4-5
Loading Graph, 4-7
When figuring weight and balance data, consideration should be given to the reduction in weight Loading Problem, Sample, 4-6
and change in moment/1000 which results from areduced fuel capacity. Long Range Fuel Tanks, 2-3
For quick re-computation of cruise performance data, use the information in the Cruise Performance Low Oil Pressure, 3-8
charts provided in the Owner'sManuals by multiplying the ENOR. HOURSand RANGE MILES figures Indicator, Fuel Quantity, 4-3
by 0.93 (for standard tank values) or 0.94 (for long range tank values); this will provide conservative Indicator, True Airspeed, 7-10
endurance and range based on the reduced fuel capacities. Inspection Requirements, 5-6 M
Pages in the Owner'sManuals which are affected by the change in fuel capacity are listed in the Instrument Markings, Engine,
chart below. 4-2 MAA Plate/Finish Trim Plate, 5-4
Instrument Panel Diagram, 1-8 Magneto Malfunction, 3-8
Insufficient Rate of Electrical Maneuvers -Normal Category, 4-1
MANUAL PAGES AFFECTED Charge, 3-9 Manifold Pressure Gage, 4-3
1973 Integrated Seat Belt/Shoulder Har- Markings, Airspeed Indicator, 4-2
OWNER'S Inside 2-1 2-2 2-14 4-6 4-7 5-8 64 6-5 6-6 6-7 6-8 7-1 Inside nesses With Inertia Reels, 2-10 Markings, Engine Instrument, 4-2
MANUAL Cover Cover Interior Care, 5-4 Master Switch, 2-3
Interior Lighting, 2-7 Maximum Glide Diagram, 6-10
OWNER'S Inside 2-1 22 2-3 2-14 4-6 4-7 6-4 6-5 6-6 6-7 6-8 Inside _Maximum Performance Climb, 1-6
MANUAL Cover Cover Maximum Performance Take-Off,
1975 L1-5
OWNER'S Inside 2-1 22 2-3 4-6 47 6-4 6-5 6-6 6-7 6-8 Inside - - Maximum Rate-Of-Climb Data
MANUAL Cover Cover Landing, 2-17 Chart, 6-3
after, 1-7 Microphone-Headset, 7-5
balked, 1-6, 2-17 Moment Envelope, Center of
THIS ADHESIVE BACKED STICKER IS TO BE ATTACHED TO ANY before, 1-6 Gravity, 4-8
BLANK PAGE IN YOUR MANUAL FOR FUTURE REFERENCE.
REFERENCE SERVICE LETTER SE 75 -7Index-3
REVISED
FUELQUANTITY
DATA
LMOD182 Fuses and Circuit Breakers, 2-6 crosswind, 2-17
1973 AIRCRAFT (SERIAL 18262251 AND ON) distance table 6-9
1974 AIRCRAFT (ALL SERIALS) '
SKYLANE 1975 AIRCRAFT (ALL SERIALS) forced, 3-1
Gnormai, 1-7, 2-17
precautionary with power, 3-2
Graph, Loading, 4-7 short field, 2-17
Due to changes in fuel tank manufacturing technique, the fuel systems in the above noted airplanes Gross Weight, inside front cover Landing Gear Servicing, inside
have been found to contain less than the capacity published in the Owner's Manuals. Data in these Ground Handling, 5-1 back cover
manuals indicates total usable capacities of 60 gallons for standard tanks and 79 gallons for long range Ground Service Plug Receptacle, main/nose wheel tire pressure,
tanks; the usable capacity per tank is shown to be 31 gallons and 39 gallons respectivelY· 7-1 inside back cover
All fuel capacity references in Owner'sManuals for these airplanes should be marked to reflect the nose gear shock strut servicing,
capacities in the chart below. inside back cover
HLet-Down, 1-6
Lighting Equipment, 2-6
TOTAL USABLE TOTAL USABLE Handling, Ground, 5-1 exterior lighting, 2-6
BOTHTANKS BOTH TANKS PER TANK PER TANK
CAPACITY Harnesses, Shoulder, 2-9, 2-10 interior lighting, 2-7
(STANDARD TANKS) 61 Gal. 56 Gal. 30.5 Gal. 29 Gal. Headset-Microphone, 7-5 Limitations, Airspeed, 4-2
CAPACITY Heating, Ventilating and Defrosting Limitations, Engine Operation,
(LONG RANGETANKS) 80 Gal. 75 Gal. 40 Gal. 37 Gal. System, Cabin, 2-8 4-2
Hot Weather Operation, 2-21 Loading Arrangements Diagram, 4-5
Loading Graph, 4-7
When figuring weight and balance data, consideration should be given to the reduction in weight Loading Problem, Sample, 4-6
and change in moment/1000 which results from areduced fuel capacity. Long Range Fuel Tanks, 2-3
For quick re-computation of cruise performance data, use the information in the Cruise Performance Low Oil Pressure, 3-8
charts provided in the Owner'sManuals by multiplying the ENOR. HOURSand RANGE MILES figures Indicator, Fuel Quantity, 4-3
by 0.93 (for standard tank values) or 0.94 (for long range tank values); this will provide conservative Indicator, True Airspeed, 7-10
endurance and range based on the reduced fuel capacities. Inspection Requirements, 5-6 M
Pages in the Owner'sManuals which are affected by the change in fuel capacity are listed in the Instrument Markings, Engine,
chart below. 4-2 MAA Plate/Finish Trim Plate, 5-4
Instrument Panel Diagram, 1-8 Magneto Malfunction, 3-8
Insufficient Rate of Electrical Maneuvers -Normal Category, 4-1
MANUAL PAGES AFFECTED Charge, 3-9 Manifold Pressure Gage, 4-3
1973 Integrated Seat Belt/Shoulder Har- Markings, Airspeed Indicator, 4-2
OWNER'S Inside 2-1 2-2 2-14 4-6 4-7 5-8 64 6-5 6-6 6-7 6-8 7-1 Inside nesses With Inertia Reels, 2-10 Markings, Engine Instrument, 4-2
MANUAL Cover Cover Interior Care, 5-4 Master Switch, 2-3
Interior Lighting, 2-7 Maximum Glide Diagram, 6-10
OWNER'S Inside 2-1 22 2-3 2-14 4-6 4-7 6-4 6-5 6-6 6-7 6-8 Inside _Maximum Performance Climb, 1-6
MANUAL Cover Cover Maximum Performance Take-Off,
1975 L1-5
OWNER'S Inside 2-1 22 2-3 4-6 47 6-4 6-5 6-6 6-7 6-8 Inside - - Maximum Rate-Of-Climb Data
MANUAL Cover Cover Landing, 2-17 Chart, 6-3
after, 1-7 Microphone-Headset, 7-5
balked, 1-6, 2-17 Moment Envelope, Center of
THIS ADHESIVE BACKED STICKER IS TO BE ATTACHED TO ANY before, 1-6 Gravity, 4-8
BLANK PAGE IN YOUR MANUAL FOR FUTURE REFERENCE.
REFERENCE SERVICE LETTER SE 75 -7Index-3

CONGRATULATIONS .......
Welcome to the ranks of Cessna owners! Your Cessna has been designed and con-
structed to give you the most in performance, economy, and comfort. It is our de-
sire that you will find flying it, either for business or pleasure, apleasant and
profitable experience.
This Owner's Manual has been prepared as aguide to help you get the most pleasure
and utility from your Model 182/Skylane. It contains information about your Cessna's
equipment, operating 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 aCessna.
World-wide, the Cessna Dealer Organization backed by the Cessna Service Depart-
ment stands ready to serve you. The following services are offered by most Cessna
Dealers:
THE CESSNA WARRANTY -- It is designed to provide you with the most
comprehensive coverage possible:
a. No exclusions
b. Coverage includes parts and labor
c. Available at Cessna Dealers world wide
d, Best in the industry
Specific benefits and provisions of the warranty plus other important
benefits for you are contained in your Customer Caré Program boak
supplied with your aircraft. Warranty service is available to you at
any authorized Cessna Dealer throughout the world upon presentation
of your Customer Care Card which establishes your eligibility under
the warranty.
FACTORY TRAINED PERSONNEL to provide you with courteous expert
service.
FACTORY APPROVED SERVICE EQUIPMENT to provide you with the
most efficient and accurate workmanship possible.
ASTOCK OF GENUINE CESSNA SERVICE PARTS on hand when you
need them.
THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING
CESSNA AIRPLANES, since Cessna Dealers have all of the Service
Manuals and Parts Catalogs, kept current 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.
Acurrent Cessna Dealer Directory accompanies your new airplane. The Directory
is revised frequently, and acurrent copy can be obtained from your Cessna Dealer,
Make your Directory one of your cross-country flight planning aids; a warm welcome
awaits you at every Cessna Dealer.

ii
=
9'-1%" MAX.
*Maximum height of airplane
with nose gear depressed, all
tires and nose strut properly
inflated, and optional flashing
beacon installed.
** ying span of airplane with
optional strobe lights installed.
PRINCIPAL
DIMENSIONS

TABLE OF CONTENTS
Page =
SECTION |=~ OPERATING CHECK LIST ..______ 11
SECTION II -DESCRIPTION AND
OPERATING DETAILS _..__.__._ 2-1
SECTION lll -EMERGENCY PROCEDURES _..__ 3-1
SECTION IV -OPERATING LIMITATIONS ........ 4-1
SECTION V-CARE OF THE AIRPLANE....____ 5-1
OWNER FOLLOW-UP SYSTEM 5-12
SECTION Vi -OPERATIONAL DATA 6-1
SECTION VIiI- OPTIONAL SYSTEMS... .__________ 7-1
This manual describes the operation and performance of both
the Cessna Model 182 and the Cessna Skylane. Equipment
described as "Optional denotes that the subject equipment
is optional on the Model 182. Much of this equipment is
standard on the Skylane model. ~
iii

Section
me Ba
OPERATING CHECK LIST
One of the first steps in obtaining the utmost performance, service,
and flying enjoyment from your Cessna is to familiarize yourself with your
airplane's equipment, systems, and controls. This can best be done by
reviewing this equipment while sitting in the airplane. Those items whose
function and operation are not obvious are covered in Section IL
Section Ilists, in Pilot's Check List form, the steps necessary to
operate your airplane efficiently and safely. It is not acheck list in its
true form as it is considerably longer, but it does cover briefly all of the
points that you should know for atypical flight. An abbreviated check list
covering the "Before Take~Off" and "Before Landing" phases of aircraft
operation is provided on aplastic card and normally stowed in the map
compartment. This abbreviated check list is aconvenient reference of
key items to be rechecked immediately prior to taxiing into position for
take-off and before entering the final approach for landing.
The flight operational characteristics of your airplane are normal
in all respects. There are no "unconventional' characteristics or oper-
ations that need to be mastered. All controls respond in the normal way
within the entiré range of operation. All airspeeds mentioned in Sections I,
II, and IIT are indicated airspeeds. Corresponding calibrated airspeeds
may be obtained from the Airspeed Correction Table in Section VI.
BEFORE ENTERING THE AIRPLANE.
(1) Make an exterior inspection in accordance with figure 1-1.
1-1

Note
Visually check aircraft for general condition during walk-
around inspection. In cold weather, remove even small
accumulations of frost, ice or snow from wing, tail and
control surfaces. Also, make sure that control surfaces
contain no internal accumulations of ice or debris. If
night flight is planned, check operation of all lights, and
make sure aflashlight is available.
©a. Remove control wheel lock.
b. Check ignition switch "OFF."
¢. Turn on master switch and check fuel quantity indicators; then
turn master switch "OFF."
d. Check fuel selector valve handle on "BOTH."
e. Check baggage door for security. Lock with key if children are
to occupy child's seat.
Figure
1-2

8
"oo
Remove rudder gust lock, if installed.
Disconnect tail tie-down.
Check control surfaces for freedom of movement and shot ke.
Check aileron for freedom of movement and security.
Disconnect wing tie-down.
Check main wheel tire for proper inflation.
Visually check fuel quantity; then check fuel filler cap secure
and vent unobstructed.
Inspect flight instrument static source opening on side of fuse-
lage for stoppage (both sides).
Check propeller and spinner for nicks and security, and pro-
peller for oil leaks.
Check carburetor air filter for restrictions by dust or other
foreign matter.
Check nose wheel strut and tire for proper inflation.
Disconnect tie-down rope.
Check oil level. Do not operate with less than nine quarts.
Fill to twelve quarts for extended flight.
Before first flight of day and after each refueling, pull out
strainer drain knob for about four seconds to clear fuel strain-
er of possible water and sediment. Check strainer drain clos-
ed. If water is observed, there is apossibility that the wing
tank sumps contain water. Thus, the wing tank sump drain
plugs and fuel selector valve drain plug should be removed to
check for the presence of water.
Check main wheel tire for proper inflation.
Visually check fuel quantity; then check fuel filler cap secure
and vent unobstructed.
Remove pitot tube cover, if installed, and check pitot tube
opening for stoppage.
Check fuel tank vent opening for stoppage.
Disconnect wing tie-down.
Check aileron for freedom of movement and security.

BEFORE STARTING THE ENGINE.
(1) Seats, Seat Belts and Shoulder Harnesses -- Adjust and lock.
(2) Brakes -- Test and set.
(3) Cowl Flaps -- "OPEN", (Move lever out of locking hole to
reposition. )
(4) Fuel Selector Valve Handle -- "BOTH".
(5) Radios and Electrical Equipment -- "OFF".
STARTING ENGINE.
@)
@)
(3)
@
(5)
(6)
(7)
Mixture -- Rich.
Carburetor Heat -- Cold.
Propeller -- High RPM.
Throttle -- Opened approximately one-half inch.
Primer -- As required.
Master Switch -- "ON".
Ignition Switch ~- "START". Hold until engine fires,
but not longer than 30 seconds (release when engine starts).
NOTE
If engine has been overprimed, start with throttle open
1/4 to 1/2 full open, Reduce throttle to idle when en-
gine fires.
NOTE
After starting, check for oil pressure indication within
30 seconds in normal temperatures and 60 seconds in
cold temperatures, If no indication appears, shut off
engine and investigate.
BEFORE TAKE-OFF.
Parking Brake -- Set.
Cowl Flaps -- Check full "OPEN".
Flight Controls -- Check for free and correct movement.
Fuel Selector Valve Handle -- "BOTH".
Elevator and Rudder Trim -- "TAKE-OFF" setting.
Throttle Setting -- 1700 RPM.
Engine Instruments and Ammeter -- Check.

(8) Suction Gage -- Check in green arc (4.6 to 5.4 inches of mercury).
(9) Magnetos ~~ Check (RPM drop should not exceed 150 RPM on
either magneto or 50 RPM differential between magnetos).
(10) Carburetor Heat -- Check operation.
(11) Propeller -- Cycle from high to low RPM; return to high RPM
(full in).
(12) Flight Instruments and Radios -- Set.
(13) Optional Autopilot or Wing Leveler -- "OFF",
(14) Cabin Doors and Window -- Closed and locked.
TAKE-OFF.
NORMAL TAKE-OFF.
(1) Wing Flaps -- 0° to 20°.
(2) Carburetor Heat -- Cold.
(3) Power -- Full throttle and 2600 RPM.
(4) Elevator Control -- Raise nose wheel at 60 MPH.
(5) Climb Speed -- 90 MPH until all obstacles are cleared, then set
up climb speed as shown in "NORMAL CLIMB" check list.
MAXIMUM PERFORMANCE TAKE-OFF.
(1) Wing Flaps -- 20°.
(2) Carburetor Heat -- Cold.
(3) Brakes -- Apply.
(4) Power -- Full throttle and 2600 RPM.
(5) Brakes -- Release.
(6) Elevator Control -- Maintain slightly tail-low attitude.
(7) Climb Speed -- 60 MPH until all obstacles are cleared, then set
up climb speed as shown in "MAXIMUM PERFORMANCE CLIMB"
check list.
(8) Wing Flaps -- Up after obstacles are cleared.
ENROUTE CLIMB.
NORMAL CLIMB.
(1) Airspeed -- 100 to 110 MPH.
(2) Power -- 23 inches and 2450 RPM.
(3) Fuel Selector Valve Handle -~ "BOTH."
(4) Mixture -- Full rich (unless engine is rough due to excessively
rich mixture).
(5) Cowl Flaps -~ Open as required.
1-5

MAXIMUM PERFORMANCE CLIMB.
(1)
(2)
(3)
(4)
(5)
Airspeed -- 89 MPH (sea level) to 85 MPH (10, 000 feet).
Power -- Full throttle and 2600 RPM.
Fuel Selector Valve Handle -- "BOTH. !"
Mixture -- Full rich (unless engine is rough).
Cowl Flaps -- Full "OPEN. "
CRUISING.
(1) Engine Power -- 1s to 23 inches of manifold pressure and 2200 -
2450 RPM.
(2)
(3)
(4)
Cowl Flaps ~- Oper as required.
Elevator and Rudder Trim -- Adjust.
Mixture -~ Lean.
LET-DOWN.
(1)
(2)
(3)
Mixture -- Rich.
Power -- As desired.
Carburetor Heat -- Apply (if carburetor icing conditions exist).
BEFORE LANDING.
Fuel Selector Valve Handle -- "BOTH."
Mixture -- Rich.
Propeller -- High RPM.
Cowl Flaps -- "CLOSED."
Carburetor Heat -- Apply before closing throttle.
Airspeed -- 80 to 90 MPH (flaps retracted).
Wing Flaps -- 0° to 40° (below 110 MPH).
Airspeed -- 70 to 80 MPH (flaps extended).
Elevator and Rudder Trim -- Adjust.
BALKED LANDING-{GO-AROUND).
®
1-6
Power -- Full throttle and 2600 RPM.

(2) Carburetor Heat -- Cold.
(3) Wing Flaps -- Retract to 20°.
(4) Cowl Flaps -- "OPEN."
(5) Upon reaching an airspeed of approximately 80 MPH, retract
flaps slowly.
NORMAL LANDING.
(1) Touchdown -- Main wheels first.
(2) Landing Roll -- Lower nose wheel gently.
(3) Braking -- Minimum required.
AFTER LANDING.
(1) Cowl Flaps -- "OPEN. "
(2) Wing Flaps -- Retract.
(3) Carburetor Heat -- Cold.
SECURING AIRCRAFT.
(1) Parking Brake -- Set.
(2) Radios and Electrical Equipment -- "OFF".
(3) Mixture -- Idle cut-off (pulled full out).
NOTE
Do not open throttle as engine stops since this actuates
the accelerator pump.
(4) Ignition and Master Switch -- "OFF".
(5) Control Lock -- Installed.
1-7

1-8
INSTRUMENT PANEL
Bis ion
wo
Bled 1
.Marker Beacon Indicator
Lights and Switches (Opt. )
.Flight Instrument Group
.Autopilot Control Unit (Opt. )
.Map Light Switch and Light
.Transponder (Opt.)
.Radios (Opt.)
.Radio Selector Switches (Opt. )
Rear View Mirror (Opt.)
Radio Selector Switch Light
Dimming Rheostat (Opt.)
.Manifold Pressure Gage
.Fuel Quantity Indicators and
Ammeter
.Cylinder Head Temperature,
Oil Temperature, and Oil
Pressure Gages
13. Over-Voltage Warning Light
14.
15. Carburetor Air Temperature
Gage (Opt. )
16. Flight Hour Recorder (Opt.)
17. Optional Radio and Instrument
Space
18. Map Compartment
19. Cabin Heat, Cabin Air and
Defroster Control Knobs
20. Cigar Lighter
21, Tachometer
22. Wing Flap Switch and
Position Indicator
23, Mixture Control Knob
24. Propeller Control Knob
25. Rudder Trim Control Wheel
Figure 2-1.
Economy Mixture Indicator (Opt.)
12
.Cowl Flap Control Handle
.Microphone (Opt. )
.Fuel Selector Valve Handle
.Elevator Trim Control Wheel
.Throttle
.Carburetor Heat Control Knob
.Electrical Switches
.Static Pressure Alternate
.Parking Brake Handle
.Circuit Breakers
.Instrument and Radio Dial
.Ignition/Starter Switch
.Engine Primer
.Phone Jack
.Master Switch
frre
rr
13
Source Valve (Opt.)
Light Rheostats

Section Il
DESCRIPTION AND OPERATING DETAILS
The following paragraphs describe the systems and equipment whose
function and operation is not obvious when sitting in the airplane. This
section also covers in somewhat greater detail some of the items listed
in Check List form in Section Ithat require further explanation.
FUEL SYSTEM.
Fuel is supplied to the engine from two tanks, one in each wing. With
the fuel selector valve on "BOTH, "" the total usable fuel for all flight con-
ditions is 60 gallons for the standard tanks and 79 gallons for opp long
range tanks.
Fuel from each wing tank flows by gravity to aselector valve. De-
pending upon the setting of the selector valve, fuel from the left, right,
or both tanks flows through a fuel strainer and carburetor to the engine
induction system.
The fuel selector valve should be in the "BOTH" position for take-off,
climb, landing, and maneuvers that involve prolonged slips or skids.
Operation from either "LEFT" or "RIGHT" tank is reserved for cruising
flight.
NOTE
When the fuel selector valve handle is in the "BOTH"
position in cruising flight, unequal fuel flow from each
tank may occur if the wings are not maintained exactly
level. Resulting wing heaviness can be alleviated
gradually by turning the selector valve handle to the
tank in the "heavy wing.
NOTE
It is not practical to measure the time required to con-
sume all of the fuel in one tank, and, after switching to
2-1

VENTED FILLER CAP
VENT
FUEL SELECTOR
LEFT FUEL TANK RIGHT FUEL TANK
To ensure maximum fuel
capacity during refueling,
place the fuel selector valve
handle in either "LEFT" or
"RIGHT" position to prevent
crossfeeding.
FUEL SYSTEM
FUEL
STRAINER ENGINE PRIMER
CODE
THROTTLE FUEL SUPPLY
(= ~CARBURETOR C2 vent
T=—a MECHANICAL
LINKAGE
fpetit
[om -
MIXTURE TO
CONTROL KNOB ENGINE
v
Figure 2-2.
2-2

the opposite tank, expect an equal duration from the
remaining fuel. The airspace in both fuel tanks is inter-
connected by a vent line (see figure 2-2) and, therefore,
some sloshing of fuel between tanks can be expected
when the tanks are nearly full and the wings are not level.
For fuel system servicing information, refer to Lubrication and Ser-
vicing Procedures in Section V.
ELECTRICAL SYSTEM.
Electrical energy is supplied by a 14-volt, direct-current system
powered by an engine-driven alternator (see figure 2-3). The 12-volt
battery-is located aft of the rear baggage compartment wall. Power is
supplied to all electrical circuits through a split bus bar, one side con-
taining electronic system circuits and the other side having general elec-
trical system circuits. Both sides of the bus are on at all times except
when either an external power source is connected or the starter switch
is turned on; then apower contactor is automatically activated to open
the circuit to the electronics bus. Isolating the electronic circuits in
this manner prevents harmful transient voltages from damaging the
transistors in the electronics equipment.
MASTER SWITCH.
The master switch is asplit-rocker type switch labeled "MASTER,"
and is "ON" in the up position and "OFF" in the down position. The
right half of the switch, labeled "BAT," controls all electrical power
to the airplane. The left half, labeled "ALT," controls the alternator.
Normally, both sides of the master switch should be used simulta-
neously; however, the "BAT" side of the switch could be turned "ON"
separately to check equipment while on the ground. The "ALT" side of
the switch, when placed in the "OFF" position, removes the alternator
from the electrical system. With this switch in the "OFF" position, the
entire electrical load is placed on the battery. Continued operation with
the alternator switch "OFF" will reduce battery power low enough to open
the battery contactor, remove power from the alternator field, and pre-
vent alternator restart.
AMMETER.
The ammeter indicates the flow of current, in amperes, from the al-
2-3

ELECTRICAL SYSTEM
REGULATOR
ALTERNATOR
£
55,
“Hee ALT RE
"CIRCUIT BREAKER
CIGAR LIGHTER
WITH CIRCUIT BREAKER]
ove. =
maser
|
KY
vourace
Swirc Senson
10 ALT REG
CIRCUIT BREAKER
Se, Fs ah
oPOLARITY GROUND
RECEPTACLE (OPT)
—SPLIT BUS
ONTACTOR
[NORMALLY
cLosen
a
FLIGHT HOUR
RECORDER (OFT)
TO INSTRUMENT
LIGHT CIRCUIT
BREAKER
sarmery 4
CONTACTOR
Y1enmony/
STARTER
SWITCH
BATTERY
MAGNETOS
CODE
@) CIRCUIT BREAKER (PUSH-TO-RESET)
@USE He 010DE AVY RESISTOR
J} CAPACITOR (NOISE FILTER)
Figure 2-3.
UX
ee
BX
5)
vem
0=-20a<40mrm
SCHEMATIC
TO LANDING &TAXI LIGHTS
TO NAVIGATION LIGHTS, GLARE
SHIELD-MOUNTED MAP LIGHT, &
OPTIONAL CONTROL WHEEL
MAP LIGHT
TO TRANSMITTER RELAY (OPT)
TO HEATED PITOT &STALL
WARNING SYSTEM (OFT)
TO FUEL OUANTITY INDICATORS,
CYLINDER HEAD TEMP. GAGE &
OPTIONAL CARBURETOR AIR
TEMPERATURE GAGE
TO IGNITION/STARTER SWITCH
TO ELECTROLUMINESCENT LIGHTING,
TO INSTRUMENT LIGHTING,
COMPASS LIGHT AND OPTIONAL
OXYGEN LIGHTING
TO OPTIONAL POST LIGHTING
TO DOME AND OPTIONAL COURTESY
LIGHTS
TO WING FLAP SYSTEM
TO FLASHING BEACON (OPT)
10 RADIO (OPT)
TO RADIO (OFF)
10 RADIO (OPT)
10 RADIO (OPT)
TO AUTOMATIC PILOT (OPT)
AUTO prOT
TO AUDIO AMPLIFIER (OPT)
FROM PRIMARY BUS
TO OVER-VOLTAGE SENSOR &
MASTER SWITCH.
TO OVER-VOLTAGE WARNING
LIGHT
TO OPTIONAL TURN.
COORDINATOR OR OPFIONAL
TURN &BANK INDICATOR
TO STALL WARNING SYSTEM
TO STROBE LIGHTS (OPT)

ternator to the battery or from the battery to the aircraft electrical sys-
tem. When the engine is operating and the master switch is "ON, '"" the
ammeter indicates the charging rate applied to the battery. In the event
the alternator is not functioning or the electrical load exceeds the output
of the alternator, the ammeter indicates the discharge rate of the battery.
OVER-VOLTAGE SENSOR AND WARNING LIGHT.
The aircraft is equipped with an automatic over-voltage protection
system consisting of an over-voltage sensor behind the instrument panel
and ared warning light, labeled "HIGH VOLTAGE", below the engine
instrument cluster.
In the event an over-voltage condition occurs, the over-voltage sen-
sor automatically removes alternator field current and shuts down the
alternator. The red warning light will then turn on, indicating to the
pilot that the alternator is not operating and the aircraft battery is supply~
ing all electrical power.
The over-voltage sensor may be reset by turning the master switch
off and back on again. If the warning light does not illuminate, normal
alternator charging has resumed; however, if the light does illuminate
again, amalfunction has occurred, and the flight should be terminated as
soon as practical.
The over-voltage warning light may be tested by momentarily turning
off the "ALT" portion of the master switch and leaving the "BAT" portion
turned on.
CIRCUIT BREAKERS AND FUSES.
Most of the electrical circuits in the airplane are protected by "push-
to-reset' circuit breakers mounted on the instrument panel. Exceptions
to this are the battery contactor closing (external power) circuit, and the
optional clock and flight hour recorder circuits which have fuses mounted
near the battery. Also, the cigar lighter is protected by amanually-
reset type circuit breaker mounted directly on the back of the lighter be-
hind the instrument panel.
When more than one radio is installed, the radio transmitter relay
(which is apart of the radio installation) is protected by the navigation
lights circuit breaker labeled "NAV LIGHTS." It is important to remem~
ber that any malfunction in the navigation lights system which causes the
circuit breaker to open will de-activate both the navigation lights and the
2-5

transmitter relay. In this event, the navigation light switch should be
turned off to isolate the circuit; then reset the circuit breaker to re-acti-
vate the transmitter relay and permit its usage. Do not turn on the navi-
gation light switch until the malfunction has been corrected.
LIGHTING EQUIPMENT.
EXTERIOR LIGHTING.
Conventional navigation lights are located in the wing tips and tail
stinger. Two landing lights are installed in the cowl nose cap. When
taxi lighting is selected, the left cowl light illuminates separately. De-
pressing the adjacent landing light switch causes both lights to illuminate
and serve as landing lights. Optional lighting includes aflashing beacon
which mounts on the top of the vertical fin, two strobe lights (one in each
wing tip), and two courtesy lights (one under each wing just outboard of
the cabin door). All exterior lights except the courtesy lights are con-
trolled by rocker-type switches located on the left switch and control panel.
The courtesy lights are operated by aswitch on the aft side of the left
rear door post.
The flashing beacon should not be used when flying through clouds or
overcast; the flashing light reflected from water droplets or particles in
the atmosphere, particularly at night, can produce vertigo and loss of
orientation.
The two high intensity strobe lights will enhance anti-collision pro-
tection. However, the lights should be turned off when taxiing in the
vicinity of other aircraft, or during flight through clouds, fog or haze.
INTERIOR LIGHTING.
Instrument and control panel lighting is provided by electrolumines-
cent lighting, flood lighting, optional post lighting and integral lighting.
Two concentric rheostat control knobs labeled "LWR PANEL, ENG-RADIO, v
and arheostat control knob labeled "INSTRUMENTS" control the intensity
of instrument and control panel lighting. Arocker-type switch labeled
1" POST-FLOOD LIGHTS" is used to select either standard flood lighting or
optional post lighting. These controls are located on the left switch and
control panel.
Switches and controls on the lower part of the instrument panel are
2-6