SkyhawK - Midtjysk Flyveklub

:
PILOT'S OPERATING HANDBOOK
c
\
.1976
SkyhawK
CESSNA MODEL 172N1
LL L
PERFORIVIANCESPECIFICATIONS
CESSNA
MODEL
PERFORMANCE SPEED:
MærimumatSeaLevel . ..
Cruiser TSVo Power at 8000 Ft
SPECI
172NT
FICATIONS
. . . . .. . . . . .
. . . . o. o. . . .
.
125 KNOTS
.
LzO
KNCIS
CRUISE: Recommended Lean Mixfure with fuel allowanee for
engine start, tæri, takeoff, elimb and 45 minutes
reserve at 45Vo power.
7lVoPowerat8000Ft. . . o . . . . ..
Fuel
75Vo Powerat8000Ft. . . . . . .
48 Gallons Usable FueI
Ma:rimumRangeatl0r000Ft . ..
38 Gallons Usable Fuel
Ma:rimumRangeatl0r000Ft . . .
48 Gallons Usable Fuel
RATEOFCLIMBATSEALEVEL . . .
SERVICECEILING. . . . . . . . . .
38 Gatlons Usable
.
. .. .
. o. .
.. .
.. .
. . .
TAKEOFF PERFORMANCE:
GroundRoll . . . . . . . . . . . . . .
TotalDistanceOverSO-FIObstacle . ..
IANDING PERFORMANCE:
GroundRoll . . . . . . . ) . . .
TotalDistanceOverS0-FtObstacle
srALL
SPEED (CAS):
FlapsUp, PowerOff . .
FlapsDown, PowerOff .
MAXIMUMWEIGHT . . . .
STANDARD EMPTY WEIGHT:
Skyhawk.
Skyhawkll
. . . . . . .
. . . . . .
MAXIMUM USEFUL LOAD:
.
.
. . . . . .
.. . . ..
. . . . . .
. . . . . .
. . . . . .
SkyhaWk. . . . . . . . .
Skyhawkll . . . . . . . .
BAGGAGEALLOWANCE . ..
WINGLOADING: Pounds/SqFt
PO\MER LOADING: Pounds/HP
FUEL CAPACITY: Total
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
' .
..
. .
. .
. .
450 NM
Range
Time
3. I HRS
595 NM
5. 1 HRS
Range
4BO
Time
4. B HRS
Time
Range
Range
Time
. . .
. . .
. . .
. . .
. .
..
. .
. .
. .
.
.
.
.
.
.
.
NM
640 NM
6. 3 IIRS
. 645 FPM
O ' 13, 100 FT
. .
. .
. .
. .
..
. .
. .
. . . . . . .
. . . . . . .
. . . . . . . . .
. . . . . . . . .
. . . . . . . O'
.. . . . . . . .
. o. . . . . . .
O
.
.
.
.
.
.
.
.
.
oILCAPACITY . . . . . . . . . . r . . . . . . . .
E"NGINE: Avco Lycoming . . . . . . . . . . . . . . .
520 FT
1250 FT
50 KNOT S
44 KNOTS
2300 LBS
1387 LBS
T4T2 LBS
913 LBS
BBB LBS
' T2O LBS
.
13.2
.
.
.
15.
3
42 GAL.
Standard Tanks
LongRangeTanks . . . . o . . . . . . . . . . .
865 FT
1525 FT
.
.
52 GA L.
8 QTS
' o-
3
20-E2D
150 BHP at 2700 RPM
PROPELLER: FixedPitch, Diameter . o . . . . . . .
D 1 0s
7- I 3-RGr-2000-
4
/ 95
.
75 IN.
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SKWffi&WK
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5es'Esi No.
1776?3'{6-
Regåsårsfioffi No.
TFåIS
Epæffi
ov- {a
I.IANDBOOK åNCLUPES THE ffiATERIAt
REQU}!RED TO BE FURESESHFM TO THE PILCIT
MY
€AR PART 3
COPYRIGHT
O 1989
CESSNA AARERAFT CffiffiPANY
WICHBTA, KÅ$€SAS, U5A
,&.
TABLE OF COIVTENTS
CESSNA
MODEL
L72I|/.{
TABLE OF CONTENTS
SECTION
. . . . . . . . . . . . . . . . .''
LIMITATIONS . . . . . . . . . . . . . . . .
CENERAL
1
.
EMERCENCYPROCEDURES..........
PERFORMANCE
3
' '' ' ' ' '
...............
NORMALPROCEDURES....
2
O
.
4
5
WEICHT & BALANCE/
EQUIPMENT LIST.
AIRPLANE E, SYSTEMS
DESCRIPTIONS
..............
AIRPLANE HANDLINC,
SERVICE
& MAINTENANCE .
.
.......
.
.......
.
SUPPLEMENTS
(Optional Systems DescriPtion
& Operating Procedures) . .
This handbool< will be keptcurrent 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. lf you are not receivi!g subscription service,
you willwant to keep in touch with your Cessna Dealer for information concerning
ihe change status of the handbook. Subsequent changes will be made in the form
of stickeis. These should be examined and attached to the appropriate page in the
handbook immediately after receipt; the handbook should not be used for operational purposes until it has been updated to a current status.
iiil(iv
blank)
SECTION
CESSNA
1
GENERAL
MODEL 1?2M
SECTION
1
CENERAL
TABI.E OF CONTENTS
Page
c . . , o o o . . . . . . . . . . ' . . . . c .
ThfgeVieW
Intro&tction . o . . . . . . . . . . . . . . . . . . . . o .
DeSCriptiveData. o . o . . o , . . . . o . . . . ' . . . .
Engine c . . . . . . o . o . . . o o . . . . . . . . .
PfOpellgf , c . . . . . . . . . . . . . . . . o . . ''. .
FUel
.
Oil.
Ir.
,
.
.
o
o
o.
.
o
.
o
..t.
.
.
t
.
.
.
"
"
r
t'
'
t
t"
'
'
I
t''
t
'
"
t"'
'
.
L-2
.
1-3
1-3
1-3
1-3
.
e
.
'
Manimum Certifieated Weights
Standard A irplane Weights
CabinandEntryDimensions. ' . . a .. . . . o . . .. .
. . . .
BaggageSpaceandEntryDimensions. ' ' . . ...
Specific Iroadings. . c . . , . . . . r . . . . a . . . . .
Symbols, AbbreviationsandTerminology. . , . . . . . . . . .
GeneratAirspeedTerminologyandSymbols' . . . . . .. .
MeteorologicalTernninology. . . . r . . .. . . ' . c . .
EnginePowgrTerminology . . . . . .. . . . c o . . . .
Airplane Performance and Flight Planning Terminol.ogy . . .
WeightandBalangeTerminology. . . . . . . , . . - . ..
1-3
t-4
L-5
1-5
x.- 5
1-5
1-5
1-6
1-6
tr.-6
1-?
l-7
L-7
1-1
SECTION 1
GENERAL
CESSNA
MODEL
1T2iyÆ
g'-9y2"filAx.
NOTES:
l.
Wing span shown with strobe lights
installed.
2.
Maximum height shown with nose
gear depressed, all tires and nose
strut properly inflated, and flashing
beacon installed.
65".
3.
Wheel '.ase length is
4.
Propeller ground clearance is 11 314".
5.
Wing area is 174 square feet.
6.
Minimum turning radius
(*pivot point
to outboard wing tip) is 27'
Figure 1-1. Three View
l-2
5T2".
SECTION
CESSNA
tr
GENERAL
MODEL 1?2M
INTRODUCTION
This handbook contains 9 sections, and includes the material required
to be furnlshed to the pitot by CAR Part 3. It also contains supplemental
data supptied by Cessna Aircraft Company.
Sectionlprovidesbasicdataandinformationofgeneralinterest.It
also contains åefinitions or explanations of symbols, abbreviations, and
terminology commonlY used'
DESCR,IPTIVE DATA
ENGINE
Number of Engines: 1.
Engine Manufacturer: Avco Lycoming.
$ngine Model Number: O-320-E2D.
Type: Normally-aspirated, direct-drive, air-cooled, lrorizontallyoppo;;d, carburetår equipped, four-cylinder engine with 320 eu. in.
f.,i"gine
-
displacement.
Horseliwer Rating and Engine Speed: 150 rated BHP at
2?00 RPM'
PROPELI,ER
Propeller Manufacfurer : McCauley A ccessory Division'
Propeller Model Number : 1C160/DTM7553.
Number of Blades: 2.
Propeller Diameter, Maximum: ?5 inches.
Minimumi 74 inehes.
Propeller Type: Fixed Pitch.
FUET
Fuel Grade (a.nd Color): 80/8? Uinimum Grade Aviation F\.rel (red).
Alternate fuels which are also approved are:
.
100/130 Low Lead AVGAS (green). (Maximum lead content of' 2 ce
per gallon. )
iOO/1SO Aviation Grade Fuel (green). (Maximum lead content of
4.6 cc per gallon. )
NOTE
-
When substituting a higher oc[ane fuel, low lead AVGAS
100 should be used whenever possible since it will result
in less lead contamination of the engine'
1-3
SECTION
CESSNA
1
GENERAI,
MODEL X.?zM
FueI Capacity;
Standard Tanks:
Total. Capacity: 42 gaLtrons.
Total Capacity Each Tank: 21 gallons.
Total Usab1e: 38 gal.X.ons"
Long Range Tanks:
TotaL Capaci.ty: 5? gatr"Ions.
Total Capacity Each Tank: 26 gallons.
Total Usable: 48 gatrlons"
NOEE
To ensure rnaxi.mum ftrel capaei.ty when nefueling, place
the fueL setreetor valve in either LEFT or RIGHT position to pr"event cross-feedi.ng"
æ8tu
Oil Grade (Speei.fiaation) :
IvmL*L-6082 Avlation Grade Stnaight Mi.neratr Oil: Use to replenish
-"supply duering first 25 hours and at the fi.rst 25*hour oi.L change.
Continue to use until a total of 50 hours has accurnuLated or oil
consuffilption has stabiliued.
NCITE
The airplane was dei.ivened fe om the factory \trith a corrosion preventi.ve aircraft engi.ne oil" This oil shoun d be
drained after the finst 25 hours of operati.on,
&{IL-L-92851 Ashåees Dispereant Oi3: This oil must be used after
first 50 hours or oi.I eonsumption has stabiffi
Recommended Våseosety For Tempenafure Range:
SAE 5CI above 16"C (60'F)"
SAE 10W30 or SAE 30 between -3.8uC (0"F) md ZtruC (?0"F').
SAE XOW3CI or SAE 2CI below *12"C(nCIoF').
NryTE
fufulti-vi.scosity oiå with a range of SAE å0W30 !s recorr!rurended for improved starting ån eold weather.
0iå eapaeity:
Sump: I Quarts"
Total: I Quarts.
x-4
SECTION
CESSNA
1
GENERAL
MODEL 172M
TIAXIflI UTI CERTIFICATED WEIGHIS
Takeoff, Normal Category: 2300 lbs.
Utility Category: 2000 lbs.
Landing, Normal Category: 2300 lbs.
Utility Category: 2000 lbs.
Weight in Baggage Compartment, Normal Category:
Baggage Area 1 (or passenger on child's seat)-StaHon 82 to 108:
120
Baggage
lbs.
See note below.
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
baggage compartment and rear seat must not be occupied.
SIANDARD AIRPTANE WEIGHIS
Standard Empty \4reight,
I\4a:<imum Useful Load:
Skyhawk:
Skyhawk
II:
S$hawk:
Skyhawk II:
138? lbs.
1412 lbs.
Category
888 lbs.
-ilfT5Norma.l
Utility Category
.Tnn5s.
588 lbs.
CABIN AND ENIRY DI'NENSIONS
Detailed dimensions of the cabin interior and entry door openings are
illustrated in Section 6.
BAGGAGE SPACE AND ENTRY DIflIENSIONS
Dimensions of the baggage area and baggage door opening are illustrated in detail in Section 6.
SPECIFIC TOADINGS
Wing Loading: 13.2 lbs. /sq.tt.
Power Loading: 15.3 tbs./hp.
tr-5
SECTION
CESSI.IA
1
MODEL I72M
GENERAL
SYMBOLS, ABBR,EVIATIONS AND TERMINOTOGY
GENERAT AINSPEED IERflIINOIOGY AND SYffIBOtS
I(CAS
Knots Calibrated Airspeed is indicated airspeed corrected
error and expressed in knots.
Knots calibrated airspeed is equal to KTAS in standard atmosphere at sea level.
KIAS
Knots lttdic.rtgd_4iTrpeqd is the speed shown on the airspeed
in knots.
KTAS
Knots True Airspeed
is the airspeed expressed in knots relir which is KCAS corrected for altitude
and temperature.
_if
is the ma;rimum
speed at which you may
vA
Maneuvering Speed
vrn
Ma;rimum FItp 4xtendsjt Speg9 is the highest speed permis-
vNo
Mæ<imum Strucfural Cruising Speed
vnn
Never Exeeed Speed is the speed limit that may not be ex-
VS
Stllting
travel.
ribed extended Position.
Speg,d
the airplane
uto
is the speed that should
, then onIY with caution'
or_ttle miqirygm g_teldy JlightjtPeel at which
is eontrollable.
Stal{ggjSjqqed gr_Lhe lginimgm s_tggly fJiqht-spegd at which
in the landing configuration at
@contiollable
the most forward center of gravity.
VX
V1,
r
,YI
Be_qt_SrgJg-of:9limb lFpeJ{is the speed wtiietr results in the
of åltifude in a given horizontal distance.
@n
Best Rate-of-ClimL-lpgsg is the speed which results in the
a given time.
ETEORO LO G IC AL
OAT
1-6
T ER
frl I N OTOGY
is the free air static temperahlre.
degrees Celsius (formerly Centigrade) or degrees Fahrenheit.
Orrtside AiLTemge_rptgle
SECTION
CESSNA
1
GENERAL
MODEL 1728[
Standard Standard
Tempera- @r
Temperahrre is 15"C at sea level pressure altitude
each 1000 feet of altitude.
ture
Pressure Pressure Altitude is the altitude read from an altimeter
subscale has been set to 29.92 inches
Altitude iffifiTffiefric
of mercury (1013 mb).
ENGINE POWER, TERfrlINOLOGY
BHP
Brake Jlo_ls_egqqel is the power developed by the engine.
RPM
Revolutions Per Minute
Static
RPM
gffi
AI
R
PtA
Static RPM is ergine speed attained during a full-throttle enrunup when the airplane is on the ground and stationary.
N E PER
Demonstrated
Crosswind
Velocity
Usable
is engine speed.
FOR'VIAN CE AND FTIGHT PtA N N IN G IERIYI IN OtO GY
Demonstrated Crosswind Velog!!' is the velocity of the crosse control of the airPlane
during takeoff and landing was actually demonstrated during
certification tests. The value shown in not considered to be
limiting.
Fuel Usable Fuel is the fuel available for flight
Unusable
planning.
Unusable Fuel is the quantity of fuel that can not be safely
Fhel
useliæfri.
GPH
Gallons Per Hour is the amount of fuel (in gallons) consumed
NMPG
Nautical Miles Per Gallon is the distance (in nautical miles)
wFiE-trctn be expected per gallon of fuel consumed at a speeific engine power setting and/or flight configuration.
g
g is acceleration due to gravitY.
W
EIGHI AN D BALANCE
Reference
TER
I{ IN OLOG Y
Reference Datum is an imaginary vertical plane from which
distances are measured for balance Flrposes.
Datum
åll liorizontal
Station
Station is a location along the airplane fuselage given in
Terrns of the distance from the reference datum.
I-7
SECTION
CESSNA
1
MODEL I72M
GENERAL
Arm
Moment
Arm is the horizontal distance from the reference dabum to
ffid-center of gravity (C. G. ) of an item.
Mornent is the product of the weight of an item multiplied by
arm. (Moment divided by the constant 1000 is used in
this handbook to simplify balanee caleulations by reducing
the number of digits. )
ITs
Center of
Gravity
(c. G. )
C. G.
Arm
C. G.
Limits
Center of Gravity is the point at which an airplane, or equipce if suspended. Its distanee 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
oments and dividing the sum by the
total weight.
Center of Gravity Limits are the extreme center of gravity
airplane must be operated at a
given weight.
Standard
Standa"d Etrlpjy-yejght
Empty
Weight
oil.
is the weight of a standard airplane,
full operating fluids and fult engine
Basic Empty Basig Empty Welght is the standard empty weight plus the
Weight
weight of optional equipment.
Useful
Useful Load is the differenee between takeoff weight and the
Load
ffiweight.
Gross
Grqsjs Jlgagg_d).Wsight
(Loaded)
Weight
is the loaded weight of the airplane.
Maximum
Takeoff
Maximum Takeoff Weight is the maxirnum weight approved
run,
Maximum
Mærimum Landing Weight is the manimum weight approved
.Weight
Landing
Weight
Tare
Tare is the weight of chocks, bloeks, stands, etc. used
nthen weighing an airplane, and is ineluded in the scale readings, Tare is deducted from the scale reading to obtain the
achral (net) airplane wei.ght.
1-8