Cessna SKYHAWK 1976 Owner's manual

PILOT'S OPERATING HANDBOOK
~
Cessna® 1976
Skyhawk
CESSNA MODEL 172M
j

PERFORMANCE -
SPECIFICATIONS
CESSNA
MODEL 172M
PERFORMANCE -SPECIFICATIONS
SPEED:
Maximum at Sea Level . . . . . . . . . . . . . . . 125 KNOTS
Cruise, 75% Power at 8000 Ft . . . . . . . . . . . . 120 KNOTS
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 . . .
38 Gallons Usable Fuel
75% Power at 8000 Ft . . .
48 Gallons Usable Fuel
Maximum Range at 10,000 Ft
38 Gallons Usable Fuel
Maximum Range at 10,000 Ft
48 Gallons Usable Fuel
RATE OF CI.JMB AT SEA LEVEL
SERVICE CEILING . . . . . . .
TAKEOFF PERFORMANCE:
Ground Roll . . . . . . . . . .
Total Distance Over 5 0-Ft Obstacle
LANDING PERFORMANCE:
Ground Roll . . . . . . . . . . .
Total Distance Over 50-Ft Obstacle
STALL SPEED (CAS):
Flaps Up, Power Off . .
Flaps Down, Power Off .
MAXIMUM WEIGHT ....
STANDARD EMPTY WEIGHT:
Skyhawk
..... . .
Skyhawk II
... . . .
MAXIMUM USEFUL LOAD:
Skyhawk ..... . .
Skyhawk II
..... .
BAGGAGE ALLOWANCE
.. .
WING LOADING:
Pounds/Sq Ft
POWER LOADING: Pounds/HP
FUEL CAPACITY: Total
Standard Tanks
Long Range Tanks .
OIL CAPACITY
ENGINE: Avco
L;c~~in~ :
150
BHP at 2700 RPM
PROPELLER: Fixed Pitch, Diameter
0 1 057 13 I ~ANO 8000 7/76
Range
Time
Range
Time
Range
Time
Range
Time
450 NM
3. 9 HRS
595 NM
5.1 HRS
480 NM
4. 8 HRS
640 NM
6. 3 HRS
645 FPM
13, 100 FT
865FT
1525 FT
520FT
1250 FT
50 KNOTS
44 KNOTS
2300 LBS
1387 LBS
1412 LBS
913 LBS
888 LBS
120 LBS
13.2
15.3
42 GAL.
52
GAL.
8 QTS
0-320-E2D
75 IN .

) I ., ()I
~ II
1976
00 El 72
S o ' o
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C S 'A AI C
V/ 10 I A
PA
SA

CONGRATULATIONS
CONGRATULATION S ..
CESSNA
MODEL 172M
..
h been designed and construct ed to
We lcome to the ranks of Cessna owners! Your Cessnaf as It ·s our desire that you will find
give you the most in performance, economy, and com ort. f ~I experience.
flying it , either for bus in ess or pleasure, a pl easant and pro It a e
. 1 et the most pleasure and utili ty
This handbook has been prepared as a guide to he P you g , ui pment operating pro-
from your a
ir plan e. It contains inf ormation about your Cessna seq W ' to re ad
· f ·t ervicing and care e urge you
cedures, and performance; and suggest i ons or I s s ·
it from cover to cover, and to refer to it frequently.
d ·th purchase
of a Cessna. World -
Our
int erest in your flying pl easure has not cease WI your
wide, the Cessna Dealer Organization backed by the Cessna Serv i ce Department stands ready
to serve you. The following serv i ces are offered by most Cessna Dealers:
THE CESSNA WARRANT Y- - It is designed to provide you with the most compre-
hensi ve cove ra ge possible:
a. No exc lu sions
b. Coverage includes parts and labor
c. Ava il able at Cessna D ealers wor ld wide
d. Best in the industry
Spec ific benefi ts and provisions of the warranty plus other important benefits for
you are contained in your Customer Care Program book suppli ed with your airplane.
Warranty service is ava il ab le to you at any authorized Cessna Dealer throughout the
world upon presentation of your Customer Care Card which establishes yo ur eli gibil-
it y under the warranty.
FACTORY TRAINED PERSONNEL to provide you with courteous expert service.
FACTORY A PPR OVED SERVI CE EQUIPMENT to provide you with the most
efficient and accurate workmanship poss ibl e.
A STOCK OF GENUI NE CESSNA SERVICE PARTS on hand when you need them.
THE LATEST AUT HORIT A TIV E IN FORMATION FOR SERVICING CESSNA
A
IRPL ANES, since Cessna Dealers have all of the Service Manuals and Parts
Catalogs,
kept current by Service Letters and Servi ce News Letters, published by
Cessna A ir craft Company.
We urge all Cessna owners to use the Cessna Dealer Organization to the fu llest.
A current Cessna Dealer Dir ec tory accompanies your new a ir plane The D. t · ·
f · 1rec ory IS rev1sed
requently, and a current copy can be obta in ed from yo ur Cessna Dealer. Mak e our
D1rectory one of your cross-country flight planning aids· a warm welco · y
every
Cessna De aler. ' me awa1 ts you at
ii

CESSNA
MODEL 172M
TABLE OF CONTENTS
TABLE OF CONTENTS
GENERAL ..
LIMITATIONS
EMERGENCY PROCEDURES
NORMAL PROCEDURES
SECTION
1
2
3
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 a nd a ttached to the appropria te 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.
iii/(iv blank)

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

SECTION 1
GENERAL
1-2
PIVOT POINT
36'
Figure 1-1. Three View
NOTES:
CESSNA
MODEL 172M
1. Wing span shown with strobe lights
installed.
2. Maxim um heig ht shown with nose
gear depressed, all tires and nose
strut properly inflated, and flashing
beacon installed.
3. Wheel '.ase length is 65".
4. Propeller ground clearance is 11 3/4".
5. Wing area is 174 square feet.
6. Minimum turning radius
(*pivot poi nt
to outboard wing tip) is 27' 5%".
*
PIVOT POINT

CESSNA
MODEL 172M SECTION 1
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.
E;ngine Model Number: 0-320-E2D.
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: 1C160/DTM7553.
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. )
NarE
When substituting a higher octane fuel, low lead AVGAS
100 should be used wh eneve r possible since it will result
in less lead contamin ation of the engine.
1-3

SECTION 1
GENERAL CESSNA
MODEL 172M
Fuel Capacity:
Oil
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.
NOfE
To ensure maximum fuel capacity when refueling , place
the fuel selector valve in either LEFT or RIGHT posi-
tion to prevent cross-feeding.
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.
MIL-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
above l6°C (60°F).
SAE 10W30 or SAE 30 between -18°C (0°F) and 21°C (70°F).
SAE 10W30 or SAE 20 below -12°C(l0°F}.
NOfE
I
Multi-viscosity oil with a range of SAE 10W30 is recom-
mended for improved starting in cold weather.
Oil Capacity:
1-4
Sump: 8
Quarts .
Total: 9 Quarts.

CESSNA
MODEL 172M SECTION 1
GENERAL
MAXIMUM CERTIFICATED WEIGHTS
Takeoff, Normal Cat e gory: 2300 lbs.
utility Category: 2000 lbs.
Landing, Norm al Categ o ry: 2300 lbs.
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 lbs.
Weight in Baggage Compartment, Utility Category: In this category, the
bag g age compartment and rear seat must not be occupied.
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight, Skyhawk: 1387 lb s.
M aximum U sefu l L oad :
Skyhawk:
Skyhawk II:
Skyhawk II: 1412 l bs .
Normal C ategory
913 lbs.
888 l bs.
CA BIN AND ENTRY DIME NSIONS
Utility Categor y
613 lbs.
588 lbs.
Detailed dimensions of t he cabi n inter i or and entry door openings are
illustrated in Section 6.
BAGGAGE SPACE AND ENTRY DIMENSIONS
Dimensions of the baggage a rea and baggage door opening are illus-
trated in detail in Section 6.
SPECIFIC LOADINGS
Wing Loading: 13. 2 lbs. /sq. ft.
Po wer Loading: 15. 3 lbs. / hp.
1-5

---....
SECTION 1
GENERAL CESSNA
MODEL 172M
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
KCAS
KIAS
KTAS
'VA
VFE
VNO
VNE
Vs
Vs
0
vx
Vy
Knots Calibrated A irs peed 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.
Knots Indicated Airspeed is the speed shown on the airspeed
indicator and expressed in knots.
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
the airplane is controllable in the landing configuration at
the most forward center of gravity.
Best Angle- of -Climb Speed is the speed wnich results in the
g reatest 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 Outside Air Temperature is the free air static temperature.
1-6
It is expressed in either degrees Celsius (formerly Centi-
grade) or degrees Fahrenheit.

CESSNA
MODEL 172M SECTION 1
GENERAL
Standard
Tempera-
ture
Pressure
Altitude
Standard Temperature is l5°C at sea level pressure altitude
and decreases by 2 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
RPM
Static
RPM
Brake Horsepower is the power developed by the engine.
Revolutions Per Minute is engine speed.
Static RPM is engine speed attained during a full-throttle en-
gine runup when the airplane is on the ground and stationary.
AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
Demon-
strated
Crosswind
Velocity
Demonstrated Crosswind Velocity is the velocity of the cross-
·wind component for which adequate control of the airplane
during takeoff and landing was actually demonstrated during
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 dist ances are measured for balance purposes.
Statio n Station is a locati on along the airplane fuselage given in
terms of the dist ance from the reference datum.
1-7

SECTION 1
GENERAL
Arm
Moment
Center of
Gravity
(C . G .)
e.G.
Arm
e.G.
Limits
Standard
Empty
Weight
CESSNA
MODEL 172M
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 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 dist a nce 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 weight of optional equipment.
Useful
Load
Gross
(Loaded)
Weight
Maximum
Takeoff
·Weight
Maximum
Landing
Weight
Tare
1-8
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
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
MODEL 172M
SECTION 2
LIMITATIONS
TABLE OF CONTENTS
Introduction . . . . . . . .
Airspeed Limitations . . . .
Airspeed Indicator Markings
Power Plant Limitations
Power Plant Instrument Markings
Weight Limits . . . . .
Normal Category . .
Utility Category . .
Center of Gravity Limits
Normal Category .
Utility Category .
Maneuver Limits
Normal Category .
Utility Category .
Flight Load Factor Limits
Normal Category
Utility Category . . .
Kinds of
Operation Limits .
Fuel Limitations
Placards ....... .
SECTION 2
LIMITATIONS
Page
2-3
2-4
2-5
2-5
2-6
2-6
2-6
2-7
2-'7
2-7
2-7
2-7
2-7
2-7
2-8
2-8
2-8
2-9
2-9
2-10
2-1/ (2-2 blank)

CESSNA
MODEL 172M 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 Ai rspeed 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. 3A12 as
Cessna Model No. 172M.
2-3

SECTION 2
LIMITATIONS
AIRSPEED LIMITATIONS
CESSNA
MODEL 172M
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 126 128 Do
not exceed this speed
Cruising Speed
except in smooth air, and
then only
with caution.
VA
Maneuvering Speed:
2300 Pounds
96 97 Do not make full or abrupt
1950 Pounds
88
89
control movements above
1600Pounds
80 80 this speed.
VFE Maximum Flap Extended
86 85
Do not exceed this speed
Speed with flaps down.
Maximum Window Open 158 160 Do
not exceed this speed
Speed with windows open.
Figure 2-1. Airspeed Limitations
2-4

CESSNA
MODEL 172M SECTION 2
LIMITATIONS
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code significance are
shown in figure 2-2.
MARKING
KIAS VALUE
SIGNIFICANCE
OR RANGE
White Arc
41-85 Full Flap Operating Range. Lower
limit is maximum weight Vs
0 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 LIMITATIONS
Engine Manufacturer: Avco Lycoming.
Engine Model Number: 0-320-E2D .
Engine Operating Limits 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: l18°C (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

SECTION 2
LIMITATIONS CESSNA
MODEL 172M
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
INSTRUMENT
MINIMUM
NORMAL CAUTION
LIMIT
OPERATING RANGE
Tachometer
At Sea Level
---
2200-
---
2500 RPM
At 5000 Ft. - - - 2200-
-- -
2600 RPM
At 10,000 Ft. -- - 2200-
- - -
2700 RPM
Oil Temperature ---
100°-245°F
-- -
Oil Pressure
25 psi 60-90 psi
---
Carburetor Air
-- - -- -
-15° to 5°C
Temperature
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:
RED LINE
MAXIMUM
LIMIT
2700 RPM
2700 RPM
2700 RPM
245°F
100
psi
---
Baggage Area 1 (or passenger on child's seat)-Station 82 to 108:
120 lbs. See note below.
2-6
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
MODEL 172M
UTILITY CATEGORY
Maximum Takeoff Weight: 2000 lbs.
Maximum Landing Weight: 2000 lbs.
SECTION 2
LIMITATIONS
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 lbs.
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°.
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

SECTION 2
LIMITATIONS CESSNA
MODEL 172M
not be occupied.
ed below:
No aerobatic maneuvers are approved except those list-
MANEUVER
Chandelles .
Lazy Eights
Steep Turns
Spins .. .
Stalls (Except Whip Stalls).
RECOMMENDED ENTRY SPEED*
105
knots
105 knots
95 knots
Slow Deceleration
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 .................. +3.8g, -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.)
2-8
*Flaps Up . . . . . . . . . . . . . . . . . . +4. 4g, -1. 76g
*Flaps Down . . . . . . . . . . . . . . . . . +3. Og
*The design load factors are 150% of the above, and in all
cases, the structure meets or exceeds design loads.