Cessna 1978 Skyhawk 172N User manual

✓- PILOT'S OPERATING HANDBOOK
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· � ssna., 
Skyhawk
CESSNA MODEL 172N
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PERFORUANCE-
SPEcIFICATIONS CESSNA
MODEL 172N
PERFORMANCE
SPECIFICATIONS
SPEED:
llarrmum at SeaLcvel 125KNOTS
Cnrise, ?Stc Pwer at 8000 Ft . L22KNOTS
CRL-ISE: Recommendedl-ean Mixture with fuel allowance for
enginestart, taxi, takeoff, climb and45 minutes
reserve at 45ac
power.
?5]r Pover at 80O0Ft . Range 485 NM
{O Gallms Us$le F\el Time 4. 1 HRS
?Str Pcner at 8000 Ft . Range 630 NM
5O
Gallons Usablel\rel Time 5.3 HRS
llaximum Rangeat 10,000 Ft Range 575NM
{OGallms Usable F\rel Time 5.7 HRS
Ilarimum Range
at 10,000 Ft Range ?50NM
5O
Gallons Us$le F\el Time ?.4 HRS
RATE OF CLIMB AT SEA LEVEL ??OFPM
SERVTCE
CEXLII,TG 14,200 FT
TAKEOFF PERFORMANCE:
Grqrnd Roll 80bFT
Totd DistanceOver 50-Ft Obstacle 1440FT
IA:fDb|3 PENFORMANCE:
Grourd Roll 520 FT
Total DistanceOver 50-Ft Obstacle 1250FT
STALL SPEED
(CAS):
PleFs Up, Power Off 50 KNOTS
fhps Dwn, Power Off . 44 KNOTS
}IATTMUM WEXGHT 23OOLBS
STAh-DARD
EMPTY WEIGHT:
Sk3rha*k
. 1379
LBS
Sk-vhawkII . 1403LBS
}TAXIML'MI,'SEFULLOAD:
Skyhawk
. 921LBS
Skyhavk II . 897 LBS
BArcAGE ALLOWANCE 120LBS
tffIIG LOADING: Pounds/SqFt 13.2
PWER I,OADING: Pounds/HP 14.
4
Ft'EL CAPACITY: Total
StandardTanks 43 GAL.
L-orgRarge Tanks 54 GAL.
orl- CAPACTTY 6 QTS
E!{GII\-E:
Avco Lycoming O-320-H2AD
160
BHP at 2700
RPM
PROPELLER: Fixed Pitch. Diameter ?5IN.
or62-r
3

 
SKYHAWK
1977 MODEL 172N
 
 
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   

 
  

3., .c, r*;q1'1 xi* *&il *
I
:'
CONGRATUI,ATIONST *)
lt, CESSNA
MODEL 1?2N
CONCRATULATIONS..
..
Welcometo theranksof Cessna
owners!YourCessna
has
beendesigned
andconstructed
togiveyou themost
inperformance,
economy,
andcomfort. lt isourdesire
thatyou will find
flyingit,either
for
businessor
pleasure,
a
pleasant
and
profitable
experience.
This
Pilot's
Operating
Handbookhasbeen
prepared
as
a
guide
to help
you
get
themost
pleasure
andutility
from
your
airplane.lt contains
information
about
your
Cessna's
equip-
ment,
operating
procedures,
and
performance;
andsuggestions
for itsservicing
andcare.We
urge
youto read
it from coverto cover,andto referto it frequently.
Our
interest
inyour flying
pleasure
has
not
ceased
withyour
purchase
of aCessna.
World-
wide,
theCessna Dealer
Organization
backedby theCessna
Customer
Services
Department
stands
readyto serve
you. The
following
services
are
offered
by mostCessna
Dealers:
THECESSNA
WARRANTY,which
provides
coverage
for parts
andlabor,
isavailable
at Cessna Dealersworldwide.
Specificbenefits
and
provisions
of warranty,
plus
other
importantbenefits
for you,
arecontained
in yourCustomer
Care
Program
book,
sup-
plied
with yourairplane.Warranty service
isavailable
to youat authorizedGessna
Dealers
throughouttheworldupon
presentation
of yourCustomer
CareCard
which
establishes
your
eligibility
underthe
warranty.
FACTORYTRAINED
PERSONNELto provideyouwithcourteous
expertservice.
FACTORY
APPROVEDSERVICEEOUIPMENT
to provide
you
efficient
andaccurate
workmanship.
A STOCK OFGENUINE
CESSNASERVICE
PARTS
onhand
when
you
need
them.
. THELATEST AUTHORITATIVE
INFORMATION
FOR
SERVICING
CESSNA
AIRPLANES,sinceCessna
Dealers
haveallof the Service
Manuals
andParts
Catalogs,
keptcurrent
by ServiceLetters andService
News
Letters,
published
by
Cessna
AircraftCompany.
Weurge
allCessna
ownersto usetheCessnaDealer
Organization
to thefullest.
A currentCessnaDealer
Directory
accompanies
your new
airplane.
TheDirectory
is
revised
frequently,anda currentcopy can
beobtained
from yourCessna
Dealer.
Make
your
Directory
one
of your cross-country
flight
planning
aids;
awarmwelcome
awaits
you
atevery
Cessna
Dealer.
11

CESSNA
MODEL 1?2N TABLE OF CONTEI.ITS
TABLE
OFCONTENTS
SECTION
CENERAL . 1
LIMITATIONS . 2
EMERCENCYPROCEDURES. . . . . . . . . . 3
NORMALPROCEDURES..
.. .... 4
PERFORMANCE.. .. 5
wErcHT& BALANCE/
EQUTPMENT
LIST.
. . . . . 6
AIRPLANE
& SYSTEMS
DESCRIPTIONS. .....7
AIRPLANEHANDLINC,
SERVICE&MAINTENANCE. .. B
SUPPLEMENTS
(Optional
Systems
Description
&OperatingProcedures) . . . 9
This handbookwill be kept current by ServiceLetters
published
by CessnaAircraft
Company. These
aredistributed to CessnaDealers
and to thosewho subscribe
through
the Owner Follow-Up
System. lf you arenot receiving subscription
service,
you will want to keepin touch with your CessnaDealer
for information concerning
the changestatus
of the handbook. Subsequent
changeswill be madein the form
of stickers. Theseshouldbeexamined
andattachedto the appropriate
page
in the
handbookimmediatelyafter receipt;the handbookshouldnot be usedfor opera-
tional purposes until it hasbeenupdated to a current status.
iiil(iv blank)

CESSNA
MODEL 172N SECTION 1
GENERAL
SECT
oN1
CEN
ERAL
TABTEOF CONIENTS
Three View
Introduction
Descriptive Data
Engine
Propeller
Fuel
oil
Murimum Certificated Weights
Standard
Airplane Weights
Cabin andEntrv Dimensions .
Baggage
Space
and Entry Dimensions . 1-5
SpecificLoadings. 1-5
Symbols, Abbreviations andTerminology 1-6
General Airspeed Terminology and Symbols. 1-6
MeteorologicalTerminology . 1-6
Engine Power Terminology L-7
Airplane Performance andFlight Planning Terminology l-7
Weight and BalanceTerminology . l-7
Page
l-2
1-3
1-3
1-3
1-3
1-3
l-4
1-5
1-5
1-5
1-1

SECTION 1
GENERAL CESSNA
MODEL 172N
rflAX.
'1. Wingspanshown
wtth strobe
lights
Installed.
2. Maxrmumherghtshown
wrth nose
gear
depressed,
all trresand nose
strut properly
Inflated,
andflashrng
beacon
Installed.
3. Wheel
baselength
ts
65"
4. Propeller
ground
clearance
s 11 3/4"
5. Wing
area
ts
174square
feet.
6. Minrmumturntng
radius
(*ptvot polnt
to outboard
wtngttp) rs27' 5lz"
*
PIVOT
POINT
l-.- ,,
Figure 1-1.
1-2
Three View

CESSNA
MODEL 172N SECTION 1
GENERAL
INTRODUCTION
This handbookcontains9 sections, and includes the material required
to be furnished to the pilot by CAR Part 3. It also contains supplemental
data suppliedby Cessna
Aircraft Company.
Section1 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: O-320-HZAD.
Engine Type: Normally-aspirated, direct-drive, air-cooled,
horizontally- opposed,carburetor equipped, four-cylinder engine
with 320cu. in. displacement.
Horsepower Rating and Engine Speed: 160 rated BHP at 27O0
RPM.
PROPETLER
Propeller Manufacturer: McCauley Accessory Division.
Propeller Model Number: 1C160/DTM7557.
Number of Blades: 2.
Propeller Diameter, Maximum: 75 inches.
Minimum: 74 inches.
Propeller Type: Fixed pitch.
FUEL
Approved FueI Grades (and Colors):
100LL Grade Aviation Fuel (Blue).
100 (Formerly 100/ 130) Grade Aviation Fuel (Green).
1-3

SECTION 1
GENERAL
FueI Capacity:
Standard Tanks:
Total Capacity: 43 gallons.
Total Capacity Each Tank: 21.5
gallons.
Total Usable: 40gallons.
Long Range Tanks:
Total Capacity: 54 gallons.
Total Capacity Each Tank: 27 gallons.
Total Usable: 50gallons.
CESSNA
MODEL 172N
NOTE
To ensure maximum fuel capacitywhen refueling, place
the fuel selector valve in either LEFT or RIGHT posi-
tion to prevent cross-feeding.
ort
Oil Grade (Specification)
:
MIL-L-6082 Aviation Grade Straight Mineral Oil: Use to replenish
supply furing first 25 hours andat the first 25-hour oil change.
Continueto use until a total of 50hours has accumulated
or oil
consumption
hasstabilized.
NOTE
The airplane was delivered from the factory with a corro-
sion preventive aircraft engineoil. This oil shouldbe
drained after thefirst 25 hours of operation.
MIL-L-22851 AshlessDispersantOil: This oil must beused after
first 50hours or oil consumption
has stabifZ6.-
Recommended Viscosity For Temperature Range:
MIL-L-6082 Aviation Grade Straight Mineral OiI:
SAE 50 above 16oC
(60oF)
SAE 40between -1oC(30'F) and 32oC(90"F).
SAE 30between-18oC
(0"F) and 21oC (70oF).
SAE 20below -LzoC
(10"F).
MIL-L-22851
Ashless Dispersant Oil:
SAE 40or SAE 50above 16oC
(60'F).
SAE 40between -1oC
(30'F) and 32oC
(90"F).
SAE 30or SAE 40between -18oC
(0"F) and 21oC
(70"F).
SAE 30below -12oC
(10"F).
Oil Capacity:
Sump: 6 Quarts.
Total: 7 Quarts (if oil filter installed).
L-4

CESSNA
MODEL 172N
Maximum Useful
Skyhawk:
Skyhawk II:
SECTION 1
GENERAL
fiT
AXIftI UfrTCERTIFICATED
WEIGHIS
Takeoff, Normal Category: 2300lbs.
Utility Category: 2000
lbs.
Landing, Normal Category: 2300 lbs.
Utility Category: 2000
lbs.
Weight in Baggage Compartment, Normal Category:
BaggageArea 1 (or passenger
on childrs seat)-station 82 to 108:
120 lbs. See
notebelow.
BaggageArea 2 -Station 108to 142: 50 lbs. See note below.
NOTE
The murimum combined
weight capacity for baggage
areas
1 and
2 is 120 lbs.
Weight in Baggage
Compartment, Utility Category: In this category,
baggagecompartment and rear seat must not be occupied.
STANDAR,D AIRPTANE WEIGHTS
Standard Empty Weight, Skyhawk:
Skyhawk II:
897
lbs.
1379
lbs.
1403
lbs.
@621lbs.
597lbs.
CABIN AND ENTRY DIfrlENSIONS
Detailed dimensionsof the cabin interior andentry door openings
are
illustrated in Section6.
BAGGAGE SPACE AND ENIRY DIftlENSIONS
Dimensions of thebaggagearea and baggagedoor openingare illus-
trated in detail in Section
6.
SPECIFICLOADINGS
Wing Loading: 13.2
lbs./sq. ft.
Power Loading: 14.4
lbs./hp.
Load:
Normal. Categor
1-5

SECTION 1
GENERAL CESSNA
MODEL 172N
SYMBOLS, ABBR,EVIATIONS
AND TERMINOTOGY
GENER,ALAIRSPEED
IERfrlINOLOGY AND SYftTBOI.S
KCAS KnotsCalibrated
Airspeed is indicated
airspeed
corrected
emor and expressed in knots.
Knots calibrated airspeed is equal to KTAS in standard at-
mosphereat sealevel.
KIAS Knots IndicatedAirspeed is the speedshown
onthe airspeed
in knots.
KTAS KnotsTrue Airspeed is theairspeedexpressedin knotsrel-
ffiir which is KCAS corrected for altitude
and temperature.
Maleuvering Speedis the maximum speed
at which you may
use abrupt control travel.
Ma:<imuLFlap E-xtended
Speedis the highest speed
permis-
sible with wing flaps in a prescribed extended
position.
Ma:<imum
Struchrral Cruising Speed
is the speed that should
, thenonly with caution.
Never Exce-gd
Speed
is the speed limit that may not be ex-
ceeded
at anytime.
Stalling Speed
or tlgminimum steady.lJight:peed at which
the airplane is controllable.
Stalling Speed
or the nginimum steady flight speedat which
the airplane is controllable in the landing configuration at
the most forward center of gravity.
Vy. Best Angle-of-CLmb Speed
is the speedwhich results in the
z1 greatest gain of altitude in a given horizontal distance.
Vy Best Rate-of-Cliqb Speed is the speed
which results in the
greatest gain in altitude in a given time.
,N
ETEORO
tO GIC
AL TER'NINOTOGY
OAT OutsideAir Temperature is the free air static temperature.
r degrees Celsius (formerly Centi-
VA
vrn
vNo
VNE
vs
uto
1-6
grade) or degrees Fahrenheit.

CESSNA
MODEL 172N
Standard
Tempera-
ture
Pressure
Altitude
SECTION 1
GENERAL
is 15"C at sealevel pressure altitude
for each 1000
feet of altihrde.
Pressure Altitude is the altitude read from an altimeter
when the altimeter's barometric scale has been set to 29.92
inches of mercury (1013
mb).
ENGINE POWER TERfiIINOtOGY
BraEe Horsepower is the power developed
by the engine.
Revolutions Per Minute is enginespeed.
Static RPM is ergine speedattainedduring a full-throttle en-
gii.e mnup whenthe airplane is on the ground and stationary.
PERFOR'VIANCE
AND FTIGHTPTANNING TER'UINOLOGY
BHP
RPM
Static
RPM
AIR
PtA NE
Demon- Demonstrated
CrosswindVelocitv is thevelocitv of the cross-
strated e control of the airplane
Crosswind during takeoff and landing was acfually demonstrated during
Velocitv certification tests. The value shown in not considered to be
Iimiting.
Usable Fuel
Unusable
Fbel
GPH
NMPG
Usable F\rel is the fuel available for flight planning.
Unusable Fuel is the quantity of fuel that can not be safely
GaA-in
Titrfri.
Gallons Per Hour is the amountof fuel (in gallons) consumed
ffi
Nautical Miles Per Gallon is the distance (in nautical miles)
gallon of fuel consumed
at a spe-
cific engine power setting and/or flight configuration.
g g is acceleration dueto gravity.
WEIGHT AND BALANCE TER'VIINOLOGY
Reference ReferenceDatum is an imaginary vertical planefrom which
Datum ffitances are measuredfor balance
purposes.
Station Station is a location along the airplane fuselage given in
Tffis of the distance from the reference datum.
t-7

SECTION 1
GENERAL CESSNA
MODEL 172N
Arm Arm is the horizontal distance from the reference dahrmto
Tfre-center
of gravity (C.
G.) of an item.
Moment Moment is the product of theweight of an item multiplied by
iis arrn- (Momentdivided by the constant1000is used in
this handbook
to simplify balancecalculations by reducing
the number of digits.)
Center of Center of Gravity is the point at which anairplane, or equip-
Gravity @ce if suspended. Its distancefrom the
(C.
G.
) reference datum is foundby dividing the total moment by the
total weight of the airplane.
C.G. Center of Gravity Arm is the arm obtained
by addingthe
Arm @oments and dividing the sum by the
total weight.
C.G. C"nt"-" of G"*ityli are the extreme center of gravity
Limits airplane must be operatedat a
given weight.
StandardSt@istheweightofastandardairpIane,
Empty @ fuII operating fluids andfull engine
Weight oil.
BasicEmpty Basic Empty Weight is the standard empty weight plus the
Weight weight of optional equipment.
Useful Useful Load is the difference betweentakeoff weight and the
Load Effipitweight.
Gross Gross (Loaded)
Weight is the loaded
weight of the airplane.
(Loaded)
Weight
Maximum Maximum Takeoff Weight is the maximum weight approved
Takeoff run.
Weight
Maximum Ma.lcimumLanding Weight is the ma:<imumweight approved
Landing
Weight
Tare Tare is theweightof chocks, blocks, stands, etc. used
iffiin weighing an airplane, and is included in the scale read-
ings. Tare is deducted
from the scale reading to obtain the
achral (net)airplane weight.
1-8

CESSNA
MODEL 172N SECTION 2 LIMITATIONS
SECTION
2
LIMITATIONS
TABLE
OF CONTENTS
Introduction
Airspeed Limitations
Airspeed Indicator IMarkings
Power Plant Limitations
Power Plant Instnrment Markings
Weight Limits
Normal Cbtegory .
Utility Ch.tegory
Center of Gravity Limits
Normal Cbtegory .
Utility Category
Page
2-3
2-4
2-5
2-5
2-6
2-6
2-6
z-7
2-7
2-7
2-7
2-7
2-7
2-7
2-8
2-8
2-8
2-9
2-9
2-LO
Maneuver Limits
Normal Ca.tegory.
Utitity Category
Flight Load Factor Limits
Normal Category
Utility Category
Kinds of Operation Limits .
FueI Limitations
Placards
2-t/ (2-2 blank)

CESSNA
MODEL 172N
INTR
OD
UCTION
SECTION 2
LIMITATIONS
Section 2 includes operating limitations, instrument markings, and
basic placards necessary for the safe operation of the airplane, its en-
gine, standard systems and standard equipment. The limitations in-
cluded in this section have been approved by the Federal Aviation
Administration. When applicable, limitations associated with optional
systems or equipment are included in Section 9.
NOTE
The airspeeds listed in the Airspeed Limitations chart
(figure 2-1) and the Airspeed Indicator Markings chart
(figure 2-2) are based on Airspeed Calibration data
shown in Section 5 with the normal static source. If the
alternate static source is being used, ample margins
should be observed to allow for the airspeed calibration
variations between the normal and alternate static sour-
ces as shown in Section 5.
Your Cessna is certificated under FAA Type Certificate No. 3,4.12
as
CessnaModel No. 172N.
2-3

SECTION 2 CESSNI
LIMITATIONS MODEL 172}
AIR,SPEED
TIMITATIONS
Airspeed limitations and their operational significance are shown in
figure 2-1.
Figure 2-1. Airspeed Limitations
SPEED KCAS KlAS REMARKS
Vlte NeverExceedSpeed 158 160 Do not exceedthis speed
in
any operation.
Vruo Maximum
Structural
Cruising
Speed 126 128 Donot exceedthis
speed
except
in smoothair,and
thenonlywith caution.
V4 Maneuvering
Speed:
2300Pounds
1950Pounds
1600Pounds
96
88
80
97
89
80
Do not make full or abrupt
control movementsabove
this speed.
Vre Maximum
FlapExtended
Speed 86 85 Do not exceedthis speed with flaps down.
Maximum
Window
Open
Speed 158 160 Do not exceedthis speed with windows open.
2-4

CESSNA
MODEL 172N SECTION 2
LIMITATIONS
AIRSPEED
INDICATOR MAR KINGS
Airspeed indicator markings andtheir color codesignificance are
shown
in figure 2-2.
Figure 2-2. Airspeed Indicator Markings
POWERPLANTTIMITATIONS
Engine Manufacturer: Avco Lycoming.
Engine Model Number: O-320-HZAD.
Engine Operating Limits for Takeoff and Continuous Operations:
Maximum Power: 160BHP.
Maximum Engine Speed: 2700 RPM.
NOTE
The static RPM range at full throttle (carburetor heat off
and full rich mixture) is 2280to 2400RPM.
Maximum Oil Temperature: 118oC
(245"F)
Oil Pressure, Minimum: 25 psi.
Maximum: 100
psi.
Propeller Manufacturer: .McCauley Accessory Di.vision.
Propeller Model Number: 1C160/DTM7557.
Propeller Diameter, Maximum: 75 inches.
Minimum: 74 inches.
MARKING KIAS
VALUE
ORRANGE SIGNIFICANCE
White
Arc 41-85 Full Flap
Operating
Range.
Lower
lirnitismaximumweight
Vgo in
landing
configuration.Upperlimit
is
maximum
speed
permissible
with
flaps
extended.
GreenArc 47
- 128 Normal
Operating
Range.Lowerlimit
ismaximum
weight
Vg at mostforward
C.G.with flaps retracted.Upper
limit
ismaximum
structural
cruising
speed.
Yellow Arc 128
- 160 Operations must be gonducted with
caution and only in smooth air.
Red
Line 160 Maximumspeed
for all
operations.
2-5

SECTION 2
LIMITATIONS CESSNA
MODEL 172N
POWER
PLANT
INSTR,U
MENT
MARKINGS
Power plant instrument markings and their color codesignificance are
shown
in figure 2-3.
INSTRUMENT REDLINE GREEN
ARC YELLOW ARC RED
LINE
MINIMUM
LIMIT NORMAL
OPERATING CAUTION
RANGE MAXIMUM LIMIT
Tachometer
Oil
Temperature
Oil Pressure
Carburetor
Air
Temperature
25 psi
2200 -
27OO
RPM
10oo-2450F
60-90psi
-150 to 5oC
27OO
RPM
2450F
100
psi
Figure 2-3. Power Plant Instrument Markings
WEIG
HT LIMIT
S
NORfrlAI CATEGORY
Maximum Takeoff Weight: 2300lbs.
Ma.:<imum
LandingWeight: 2300
lbs.
Maximum Weight in Baggage
Compartment:
Baggage
Area 1 (or passenger
on child's seat)-Station82to 108:
120lbs. Seenote below.
Baggage
Area 2 -Station 108
to 142:50 lbs. See notebelow.
NOTE
The maximum combined weight capacity for baggage
areas
1 and 2 is 120lbs.
2-6

CESSNA
MODEL 172N SECTION 2
LIMITATIONS
UTIIITY CATEGORY
Maximum Takeoff Weight: 2000 lbs.
Maximum Landing Weight: 2000 lbs.
Maximum Weight in BaggageCompartment: In the utility category, the
_ baggagecompartment andrear seat must not be occupied.
CENTER
OF GRAVITYTIMITS
NON,iAAL CAIEGON,Y
Centerof Gravity Range:
Forward: 35. 0 inches
aft of dah.rmat 1950 lbs. or less, with straight
line variation to 38.5 inches aft of datum at 2300lbs.
Aft: 47.3 inchesaft of datum
at all weights.
Reference Datum: Lower portion of front face of firewall.
UTIIITY CATEGORY
Centerof Gravity Range:
Forward: 35.
0 inches
aft of datumat 1950lbs. or less, with straight
line variation to 35.
5 inchesaft of datumat 2000
lbs.
Aft: 40.5 inchesaft of datumat all weights.
ReferenceDatum: Lower portion of front face of firewall.
MANEUVER
LIMITS
NOR,IUAt CATEGOR,Y
This airplane is certificated in both the normal and utility catego-
ry. The normal category is applicable to aircraft intended for non-
aerobatic operations. These include any maneuvers incidental to nor-
mal flying, stalls (except whip stalls), Lazy eights, chandelles, and
turns in which the angle of bank is not more than 60o. Aerobatic ma-
neuvers, including spins, are not approved.
UTIIIIY CATEGOR,Y
This airplane is not designed
for purely aerobatic flight. However,
in the acquisitionof various certificates such as commercial pilot, instru-
ment pilot andflight instructor, certain maneuvers are required by the
FAA. A11 of these maneuversare permitted in this airplane whenoper-
ated in the utility category.
2-7

SECTION 2
LIMITATIONS CESSNA
MODEL 172N
RECOMMENDEDENTRY SPEED*
105knots
. 105 knots
95lmots
In theutility category, the baggage
compartment and rear seatmust
not be occupied. No aerobatic maneuvers are approvedexcept thoselist-
edbelow:
IVIANEWER
Chandelles.
Lazy Eights
SteepTurns
Spins SlowDeceleration
Stalls (ExceptWhip Stalls). SIow
Deceleration
*Abrupt use of the controls is prohibited above97 knots.
Aerobatics that may impose high loads shouldnot be attempted. The
important thing to bear in mind in flight maneuvers is that the airplane is
clean in aerodynamic design andwill build up speed
quickly with the nose
down. Proper speed
control is an essential requirement for execution
of
any maneuver, andcare shouldalways be exercised to avoid excessive
speed
which in turn can impose excessive loads. In the executionof all
maneuvers, avoid abruptuse of controls. Intentional spins with flaps ex-
tendedare prohibited.
FLIGHT LOAD FACTOR LIMITS
NOR'Y\At CATEGO
RY
Flight Load Factors (Gross
Weight- 2300
lbs.
):
*Flaps Up . +3.8g, -L.52g
*Flaps Down. +3.0g
*The design loadfactors are l50voof the above, andin aII
cases, thestruch.rre
meetsor exceeds
designloads.
UTITITY CATEGORY
Flight Load Factors (Gross Weight - 2000lbs.):
+Flaps
Up +4.49, -1.?69
*Flaps Down. +3.0g
*The design load factors are L50Voof the above, andin all
cases, the structure meetsor exceeds designloads.
2-B