Cessna SKYHAWK 1976 Owner's manual

<" PILOT'S OPERATING HANDBOOK
Ce~a. 1976< ...
...... ~ . ,
Skyhawk
CESSNA MODEL 172M
'"
1

PERFORMANCE- CESSNA
SPECIFlCATIONS MODEL 172M
PERFORMANCE - SPECIFICATIONS
SPEED:
Maximum at Sea Level . . . . . . . . . . . . . . . 125 KNOTS
Cruise, 75% Power at 8000 Ft ............ 120 KNors
CRUISE: Recommended Lean Mixture with fuel allowance for
engine start, taxi, takeoff, climb and 45 minutes
reserve at 45% power.
75% Power at 8000 Ft. . Range 450
NM
38 Gallons Usable Fuel Time
3.9 HRS
75% Power at 8000 Ft. . . . Range 595
NM
48
Gallons Usable Fuel Time
5.1 HRS
Maximum Range at 10,000 Ft Range 480
NM
38 Gallons Usable Fuel Time
4.8 HRS
Maximum Range at 10,000 Ft Range 640
NM
48 Gallons Usable Fuel Time
6.3 HRS
RATE OF CLIMB AT SEA LEVEL 645
FPM
SERVICE CEILING . . . . . . .
13,100 FT
TAKEOFF PERFORMANCE:
Ground
Roll . . . . . . . • 865
FT
Total Distance Over 50-Ft Obstacle
1525 FT
LANDING PERFORMANCE:
Ground Roll
.......•...
520 FT
Total Distance Over 50-Ft Obstacle
1250 FT
STALL SPEED (CAS):
Flaps Up, Power Off . . . 50
KNors
Flaps Down, Power Off . . 44 KNOTS
MAXIMUM WEIGHT . . . . . 2300 LBS
STANDARD
EMPTY WEIGHT:
Skyhawk
...... . 1387 LBS
Skyhawk
II ..... . 1412 LBS
MAXIMUM USEFUL LOAD:
Skyhawk
•...... 913 LBS
Skyhawk
II ..... . 888 LBS
BAGGAGE ALLOWANCE
.. . 120 LBS
WING LOADING: Pounds/Sq Ft
13.2
POWER LOADING: Pounds/HP
15.3
FUEL CAPACITY: Total
Standard Tanks
• 42 GAL.
Long Range Tanks . . 52 GAL.
OIL CAPACITY . . . . . 8 QTS
ENGINE: Avco
Lycoming.
0-320-E2D
150 BHP at 2700 RPM
PROPELLER: Fixed Pitch, Diameter
75 IN.
DI057-13-RGI-2000-4/95

PILOT'S OPERATING HANDBOOK
~
Cessna.
SKYHAWK
1976 MODEL 172M
Serial No. _~ ____ _
Registration No. ____ _
THIS HANDBOOK INCLUDES THE MATERIAL
REQUIRED TO
BE FURNISHED TO THE PILOT
BY CAR PART 3
COPYRIGHT @ 1989
CESSNA AIRCRAFT COMPANY
WICHIT A, KANSAS, USA

CONGRA TULA TIONS
CESSNA
MODEL 172M
CONGRATULATIONS .. ..
Welcome to the ranks of Cessna owners! Your Cessna has been designed and constructed to
give you the most in performance, economy, and comfort. It is our desire that you will find
flying it, either for business
or pleasure, a pleasant and profitable experience.
This handbook has been prepared as a guide
to help you get the most pleasure and utility
from your airplane. It contains information about your Cessna's equipment, operating pro-
cedures, 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 Cessna Dealer Organization backed by the Cessna Service Department 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 compre-
hensive 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 Care Program book supplied with your airplane.
Warranty service
is available to you at any authorized Cessna Dealer throughout the
world upon presentation of your Customer Care Card which establishes your eligibil-
ity 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.
A STOCK OF GENUINE CESSNA SERVICE PARTS on hand when you need them.
THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING CESSNA
AI RPLANES, 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.
A current Cessna 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 aids; a warm welcome awaits you
at
every Cessna Dealer.

CESSNA
TABLE OF CONTENTS
MODEL 172M
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
This handbook will be kept current by Service Letters published by Cessna Aircraft
Company. These are distributed
to Cessna Dealers and to those who subscribe
through the Owner Follow-Up System. If you are not receiving subscription service,
you will want
to keep in touch with your Cessna Dealer for information concerning
the change status of the handbook. Subsequent changes
will be made in the form
of stickers. These should be examined and attached to the appropriate page in the
handbook immediately after receipt; the handbook should not be used for opera-
tional purposes until it has been updated
to a current status.
m!(iv blank)

\
CESSNA
SECTION 1
MODEL 172M GENERAL
SECTION 1
GENERAL
TABLE OF CONTENTS Page
Three View . . . 1-2
Introduction . . . 1-3
Descriptive Data. 1-3
Engine . 1-3
Propeller . . 1-3
Fuel . . . • 1-3
enl . . . . . 1-4
Maximum Certificated Weights 1-5
Standard Airplane Weights 1-5
Cabin and Entry Dimensions. . 1-5
Baggage Space and Entry Dimensions. 1-5
SpecifiC Loadings. . . . . . . . . . 1-5
Symbols, Abbreviations and Terminology. 1-6
General Airspeed Terminology and Symbols. 1-6
. . . . • . . 1-6 Meteorological Terminology.
Engine Power Terminology . . . . . . . . 1-7
Airplane Performance and Flight Planning Terminology 1-7
Weight and Balance Terminology. . . . • . . . . . . 1-7
1-1

/ SECTION 1 CESSNA
GENERAL MODEL 172M
NOTES;
t. Wing span shown with strobe lights
installed.
2. Maximum height shown with nose
gear depressed, all tires and nose
strut properly tnflated, and trashing
beacon installed,
3. Wheel '.ase length is 65",
4. Propeller ground clearance is 11 314",
6. Wing area is 174 square feet.
6. Minimum turning radius l*pivGt point
to out.b09rd wino tip) is 21' 5%".
PIVOT POINT PIVOT POINT
* *
36'
Figure 1-1. Three View
1-2

CESSNA SECTION 1
MODEL 172M GENERAL
INTRODUCTION
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 definitions or explanations of symbols, abbreviations, and
terminology commonly used.
DESCRIPTIVE DATA
ENGINE
Number of Engines: 1.
Engine Manufacturer: Avco Lycoming.
Engine Model
Number: 0-320-E20.
Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally-
opposed, carburetor equipped, four-cylinder engine with 320 cu. in.
displacement.
Horsepower Rating and Engine Speed: 150 rated BHP at 2700 RPM.
PROPELLER
Propeller Manufacturer: McCauley Accessory Division.
Propeller Model Number: lC160/0TM7553.
Number of Blades: 2.
Propeller Diameter, Maximum: 75 inches.
Minimum: 74
inches.
Propeller Type: Fixed pitch.
FUEL
Fuel Grade (and Color): 80/87 Minimum Grade Aviation Fuel (red).
Alternate fuels which are also approved are:
100/130 Low Lead AVGAS (green). (Maximum lead content of 2 cc
per gallon. )
100/130 Aviation Grade Fuel (green). (Maximum lead content of
4. 6
cc per gallon. )
NOTE
When
substituting a higher octane fuel, low lead AVGAS
100 should be used whenever possible since it will result
in less lead contamination of the engine.
1-3

1-4
SECTION 1
CESSNA
GENERAL MODEL 172M
Fuel Capacity:
Standard
Tanks:
Total Capacity: 42 gallons.
Total Capacity Each Tank: 21 gallons.
Total Usable: 38 gallons.
Long Range Tanks:
Total Capacity: 52 gallons.
Total Capacity Each Tank: 26 gallons.
Total Usable: 48 gallons.
NOTE
To
ensure maximum fuel capacity when refueling, place
the fuel
selector valve in either LEFT or RIGHT posi-
tion to prevent cross-feeding.
OIL
Oil Grade (Specification):
:M1L-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.
:M1L-L-22851
Ashless Dispersant Oil: This oil must be used after
first 50 hours or oil consumption has stabilized.
Recommended Viscosity For Temperature Range:
SAE
50 aoove t6°C (60°F).
SAE IOW30 or SAE 30 between -18°C (O°F) and 21°C (70°F).
SAE 10W30 or SAE 20 below -12°C(10°F).
NOTE
Multi-viscosity oil with a range of SAE 10W30 is recom-
mended for improved starting in cold weather.
Oil Capacity:
Sump: 8
Quarts.
Total: 9 Quarts.

CESSNA
SECTION 1
MODEL 172M GENERAL
MAXIMUM CERTIFICATED WEIGHTS
Takeoff, Normal Category: 2300 lbs.
Utility Category: 20001bs.
Landing, Normal Category: 23001bs.
utility Category: 2000 lbs.
Weight in Baggage Compartment, Normal Category:
Baggage Area 1 (or passenger on child's seat)-Station 82 to 108:
120 lbs. See note below.
Baggage
Area 2 -Station 108 to 142: 50 lbs. See note below.
NOTE
The maximum combined weight capacity
for baggage areas
1 and 2 is 120 Ibs.
Weight in Baggage
Compartment, Utility Category: In this category, the
baggage
compartment and rear seat must not be occupied.
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight, Skyhawk: 1387 lbs.
Skyhawk
ll: 1412 lbs.
Maximum Useful Load:
Skyhawk:
Normal Category
913 ths.
Utilit! Category
6 3 lbS.
Skyhawk II: 8881bs.
588 Ibs.
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 illus-
trated in detail in Section 6.
SPECIFIC LOADINGS
Wing Loading: 13.2 lbs. /sq. ft.
Power Loading: 15. 3 Ibs. /hp.
1-5

1-6
SECTION 1
CESSNA
GENERAL MODEL
172M
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
KCAS
Knots Calibrated Airspeed is i!1dicated airspeed corrected
for position and instrument error and expressed in knots.
Knots
calibrated airspeed is equal to KTAS in standard at-
mosphere at sea level.
KIAS
Knots Indicated
Airspeed is the speed shown on the airspeed
indicator and expressed in knots.
KTAS Knots
True Airspeed is the airspeed expressed in knots rel-
ative to undisturbed air which is KCAS corrected for altitude
and
temperature.
Maneuvering Speed is the maximum speed at which you may
use abrupt control travel.
Maximum Flap Extended Speed is the highest speed permis-
sible 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 the speed limit that may not be ex-
ceeded at any time.
stalling Speed or the minimum steady flight speed at which
the
airplane is controllable.
Stalling Speed
or the minimum steady flight speed at which
Vs
o the
airplane is controllable in the landing configuration at
the most forward center of gravity.
Best Angle-oi-Climb Speed is the speed wliich results in the
greatest gain of altitude in a given horizontal distance.
Vy
Best Rate-oi-Climb Speed is the speed which results in the
greatest gain in altitude in a given time.
METEOROLOGICAL TERMINOLOGY
OA T Outside A ir Temperature is the free air static tempera~re.
It is expressed in either degrees Celsius (formerly CentI-
grade) or degrees Fahrenheit.

CESSNA SECTION 1
MODEL 172M
GENERAL
Standard
Tempera-
ture
Pressure
Altitude
Standard Temperature is 15°C at sea level pressure altitude
and decreases by 2b C for each 1000 feet of altitude.
Pressure Altitude is the altitude read from an altimeter
when the barometric subscale has been set to 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-throttle en-
RPM gine
runup when the airplane is on the ground and stationary.
AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
Demon- .Demonstrated Crosswind Velocity is the velocity of the cross-
strated
wind component for which adequate control of the airplane
Crosswind
during takeoff and landing was actually demonstrated during
Velocity
certification tests. The value shown in not considered to be
limiting.
Usable
Fuel Usable Fuel is the fuel available for flight planning.
Unusable
Fuel
GPH
NMPG
g
Unusable Fuel is the quantity of fuel that can not be safely
used in flight.
Gallons
Per Hour is the amount of fuel (in gallons) consumed
per hour.
Nautical Miles Per Gallon is the distance (in nautical miles)
which can be expected per gallon of fuel consumed at a spe-
cific engine power setting and/or flight configuration.
£ is acceleration due to gravity.
WEIGHT AND BALANCE TERMINOLOGY
Reference Reference Datum is an imaginary vertical plane from which
Datum
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.
1-7

1-8
SECTION 1
GENERAL
Arm
Moment
Center of
Gravity
(C. G.)
C.G.
Arm
C. G.
Limits
Standard
Empty
Weight
CESSNA
MODEL 172M
Arm is the horizontal distance from the reference datum to
theCenter 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 handbook to simplify balance calculations by reducing
the
number of digits. )
Center of Gravity is the point at which an airplane, or equip-
ment, would balance if suspended. Its distance 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
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 airplane,
including unusable fuel, full operating fluids and full engine
oil.
Basic Empty Basic Empty Weight is the standard empty weight plus the
Weight
Useful
Load
Gross
(Loaded)
Weight
Maximum
Takeoff
Weight
Maximum
Landing
Weight
Tare
weight of
optional equipment.
Useful Load is the difference between takeoff weight and the
basic empty weight.
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
Wilen 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
SECTION 2
MODEL 172M LIMITATIONS
SECTION 2
LIMITATIONS
TABLE OF CONTENTS
Page
Introduction • • . . • . . •
2-3
Airspeed Limitations . . . . 2-4
Airspeed Indicator Markings
2-5
Power Plant Limitations • .
2-5
Power Plant Instrument Markings
2-6
Weight
Limits • • . • . 2-6
Normal Category. . 2-6
utility Category . • •
2-7
Center of Gravity Limits
2-7
Normal Category. •
2-7
Utility Category •
2-7
Maneuver Limits
2-7
Normal Category •
2-7
Utility Category .
2-7
Flight Load Factor Limits
2-8
Normal Category
2-8
Utility Category • • •
2-8
Kinds of Operation Limits •
2-9
Fuel Limitations
2-9
Placards •.•..•..
2-10
2-1/(2-2 blank)

CESSNA
SECTION 2
MODEL 172M LIMITA TIONS
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.
NOI'E
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 alter-
nate static source is being used, ample margins should
be
observed to allow for the airspeed calibration varia-
tions between the normal and alternate static sources as
shown in Section 5.
Your Cessna is certificated under FAA Type Certificate No. 3A 12 as
Cessna Model No. 172M.
2-3

2-4
SECTION 2
CESSNA
LIMITATIONS MODEL 172M
AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown in
figure 2-1.
SPEED KCAS KIAS
REMARKS
VNE
Never Exceed Speed 158 160 Do
not exceed this speed in
any operation.
VNO
Maximum Structural
Cruising Speed 126 128 Do
not exceed this speed
except
in smooth air, and
then only with caution.
VA
Maneuvering Speed;
2300 Pounds
1950 Pounds
1600 Pounds
96
88
80
97
89
80
Do not make full or abrupt
control movements above
this speed.
VFE Maximum Flap Extended
Speed
86 85
Do not exceed this speed
with flaps down.
Maximum Window Open
Speed
158
160 Do
not exceed this speed
with windows open.
Figure 2-1. Airspeed Limitations

CESSNA SECTION 2
MODEL 172M LIMITATIONS
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code significance are
shown in figure 2-2.
MARKING KIAS VALUE
OR RANGE SIGNIFICANCE
White Arc
41 - 85 Full Flap Operating Range. Lower
limit is maximum weight VSo in
landing configuration. Upper
limit
is maximum speed permissible with
flaps extended.
Green Arc
47 128 Normal Operating
Range. Lower
limit is maximum weight Vs with
flaps retracted. Upper
limit is maxi-
mum structural cruising
speed.
Yellow Arc 128 -160 Operations must
be \=onducted with
caution
and only in smooth air.
Red Line 160 Maximum
speed for all operations.
Figure 2-2. Airspeed Indicator Markings
POWER PLANT LI MIT AllONS
Engine Manufacturer: Avco Lycoming.
Engine Model Number:
0-320-E2D.
Engine Operating lJ.mits for Takeoff and Continuous Operations:
Maximum Power: 150 BHP.
Maximum Engine Speed: 2700 RPM.
NOTE
The
static RPM range at full throttle (carburetor heat
off)
is 2300 to 2420 RPM.
Maximum
Oil Temperature: l1SoC (245°F).
Oil Pressure, Minimum: 25 psi.
Maximum: 100 psi.
Propeller Manufacturer: McCauley Accessory Division.
Propeller Model Number: 1C160/DTM7553.
Propeller Diameter, Maximum: 75 inches.
Minimum:
74 inches.
2-5

2-6
SECTION 2 CESSNA
LIMITATIONS MODEL 172M
POWER PLANT INSTRUMENT MARKINGS
Power plant instrument markings and their color code significance are
shown in figure 2-3.
INSTRUMENT
RED LINE GREEN ARC YELLOW ARC
RED LINE
MINIMUM
LIMIT
NORMAL
OPERATING CAUTION RANGE MAXIMUM
LIMIT
Tachometer
At Sea Level
At 5000 Ft.
At 10,000 Ft.
Oil Temperature
Oil
Pressure
Carburetor Air
Temperature
---
---
-
--
25 psi
- -
2200 -
2500
RPM
2200 -
2600
RPM
2200
2700
RPM
100°-245°F
60-90
psi
---
- -
--
---
--
--
-15° to 5°C
2700
RPM
2700 RPM
2700 RPM
245°F
100
psi
---
Figure 2-3. Power Plant Instrument Markings
WEIGHT LIMITS
NORMAL CATEGORY
Maximum Takeoff Weight: 2300 lbs.
Maximum Landing Weight: 2300 lbs.
Maximum Weight in Baggage Compartment:
Baggage Area 1 (or passenger on child's seat)-Station 82 to 108:
120
lbs. See note below.
Baggage
Area 2 -Station 108 to 142: 50 lbs. See note below.
NOTE
The maximum combined weight capacity for baggage areas
1 and 2 is 120 lbs.

CESSNA SECTION 2
MODEL 172M LIMITATIONS
UTILITY CATEGORY
Maximum Takeoff Weight: 2000 lbs.
Maximum Landing Weight: 2000 lbs.
Maximum Weight
in Baggage Compartment: In the utility category. the
baggage compartment and rear seat must not be occupied.
CENTER OF GRAVITY LIMITS
NORMAL CATEGORY
Center of Gravity Range:
Forward: 35.0 inches aft of datum at 1950 lbs. or less, with straight
line variation to 38. 5 inches aft of datum at 2300 Ibs.
Aft:
47.3 inches aft of datum at all weights.
Reference Datum: Front face of firewall.
UTILITY CATEGORY
Center of Gravity Range:
Forward: 35.0 inches aft of datum at 1950 lbs. or less, with straight
line variation to 35. 5 inches aft of datum at 2000 lbs.
Aft:
40.5 inches aft of datum at all weights.
Reference Datum: Front face of firewall.
MANEUVER LIMITS
NORMAL CATEGORY
This airplane is certificated in both the normal and utility category.
The normal category is applicable to aircraft intended for non-aerobatic
operations. These include any maneuvers incidental to normal flying,
stalls (except whip stalls) and turns in which the angle of bank is not more
than 60
0 •
UTILITY CATEGORY
This airplane is not designed for purely aerobatic flight. However,
in the
acquisition of various certificates such as commercial pilot, instru-
ment pilot and flight instructor, certain maneuvers are required by the
FAA.
All of these maneuvers are permitted in this airplane when oper-
ated in the utility category.
In the utility category, the baggage compartment and rear seat must
2-7

2-8
SECTION 2
CESSNA
LIMITATIONS MODEL 172M
not be occupied.
No aerobatic maneuvers are approved except those list-
ed below:
MANEUVER RECOMMENDED ENTRY SPEED*
Chandelles . ·
... 105 knots
Lazy Eights ·
... 105 knots
Steep
Turns
· . .. 95 knots
Spins
...
Slow Deceleration
Stalls (Except Whip Stalls). Slow Deceleration
*Abrupt use of the controls is prohibited above 97 knots.
Aerobatics that may impose high loads should not be attempted. The
important thing to bear in mind in flight maneuvers is that the airplane is
clean in aerodynamic design and will build up speed quickly with the nose
down.
Proper speed control is an essential requirement for execution of
any maneuver, and
care should always be exercised to avoid excessive
speed which in turn can impose excessive loads. In the execution of all
maneuvers, avoid abrupt use of controls. Intentional spins with flaps ex-
tended are prohibited.
FLIGHT LOAD FACTOR LIMITS
NORMAL CATEGORY
Flight Load Factors (Gross Weight -2300 lbs.)
*Flaps Up .................. +3. Sg, -1. 52g
*Flaps Down ................. +3. Og
*The design load factors are 150% of the above, and in all
cases, the structure meets or exceeds design loads.
UTILITY CATEGORY
Flight Load Factors (Gross Weight -2000 lbs. )
*Flaps Up . . . • . . . . . . . . . . . . . . +4.4g, -1.76g
*Flaps Down ................. +3.0g
*The design load
factors are 150% of the above, and in all
cases, the structure meets or exceeds design loads.