Cessna Hawk XP R172K Owner's manual

CESSNA MODEL R172K
p'LOiT'S OPERATING HAN~BOOK
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PERFORMANCE - SPEC\F\CArl~ \ \ I'.
PERFORMANCE-
SPECIFICA TIONS
SPEED:
Maximum at Sea Level . . . . . . . . . . . . . . .
Cruise, 80% power at 6000 Ft . . . . . . . . . . . .
CRUISE: Recommended Lean Mixture with fuel allowal'ce rill
engine start, taxi, takeoff, climb and 45 minuLeH
reserve at 45% power.
80% power at 6000 Ft. . . .
49 Gallons Usable Fuel
Maximum Range at 10,000 Ft
49 Gallons Usable Fuel
RATE OF CLIMB AT SEA LEVEL
SERVICE CEILING .....
TAKEOFF PERFORMANCE:
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Rangl'
Time
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Range
Time
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Ground Roll . . . . . .
Total Distance Over 50- Ft Obstacle
LANDING PERFORMANCE:
Ground Roll . . . . . . . . . . .
Total Distance Over 50-Ft Obstacle
8TALL SPEED (CAS):
Flaps Up, power Off ..
Flaps Down, power Off .
MAXIMUMWEIGHT . . . .
STANDARD EMPTY WEIGHT:
Hawk XP .
Hawk XP II .
MAXIMUMUSEFUL LOAD:
Hawk XP .
Hawk XP II .
\lAGGAGE ALLOWANCE .
WING LOADING: pounds/Sq Ft
1'( lWER LOADING: pounds/HP
I"\IKL CAPACITY: Total .
<1I1,CAPACITY .
I':N<:INE: Teledyne Continental, Fuel Injection
1!15BHP at 2600 RPM
'll'l':LLER: Constant Speed, Diameter ...
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PILOT'S OPERATING HANDBOOK
Ce~a@
HAWK XP
1977 MODEL R172K
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Serial No.lS 17:.-t~ 33.')
Registration No.;1I9{18/ 11\
THIS HANDBOOK
REQUIRED TO BE INCLUDES THE MATERIAL
BY CAR PART 3 FURNISHED TO THE PILOT
CESSNA AiRCR'AFij~OMPANY
WICHITA, KANSAS, USA

CON( :IU\,\,UI.ATIONS
CESflll/\
MODEL R177,1'
CONGRATULATIONS. · · ·
Welcome to the ranks of Cessna owners! Your Cessna has been designed and constructed
to\)ive you the most in performance, econon1V, and comfort. It is our desire that you will find
lIying it, either for business or pleasure, a plea'''lflt and profitable experience.
This Pilot's Operating Handbook has been prepared us a quirle to help you get the most
.luasure and utility from your airplane. II contains in{olillalion about your Cessna's equip-
\ i'O<, "","""9 p"e",",~, and "ecf",m""'" and ;o","",i,,'" ior its ~Ni"", and care, We
\ <111 yoJ to read it from cover 10 cover, and to refer to it frequently.
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II A' i ,i',r"~. in y,,'" flyi", p'e~"",~ not ceased wi<, vou p"",ew of "Coo""" Wool"
': ,,\ I', I].essna Dealer Organization backed ov the Cessna Customer Services Department
,I, n./~ady., to serve you. The followmg serVices are offered by most Cessna Dealers:
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iTHE CESSNA WARRANTY, which provides coverage for parts and labor, is available
a 'oM"" 0"\,,, woddw ide Sp" iflc b""li" and provisions of werran'y, 1""' 0 <boo'
,important benefits for you, are contained in your Customer Care Program book, sup
••• ' plied with your airplane. Warranty service is available to you at authorized Ces';II"
, Dealers throughout the world upon presentation of your Customer Care Card Whll I I
e5tablishes your eligibility under the warranty.
FACTORY TRAINED PERSONNEL to provide you with courteo
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FACTORY APPROVED SERVICE EQUIPMENT to provide you "lIici,,"1 alKI acclIl.llt·
workmanship.
A STOCK OF GENUINE CESSNA SERVICE PARTS Oil halld when you need them.
fI 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.
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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 fiight planning aids; a warm welcome awaits you
at every Cessna Dealer.
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CI':S:.,NA
MODEL IU72K
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TABLE OF CONTENTS
SECTION
CENERAL
LIMITATIONS
EMERCENCY PROCEDURES
NORMAL PROCEDURES
PERFORMANCE
...
WEleHT& BALANCE/
EQUIPMENT LIST.
. ..
1
2
3
4
5
AIRPLA~,IE (~ SYSTEMS
DESCRIPTIONS. .
HANDLINe
6( /vtAIN1!ENANCE

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SECTION 1
GENERAL
Three View
Introduction
Descriptive Data
Engine
Propeller
Fuel ..
Oil
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 . . . . .
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TABLE OF CONTENTS
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SECTION 1
GENERAL
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MODEL R172K
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INTRODUCTION
This handbook contains 9 sections, and includes the material re-
quired 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
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II
ENGINE
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Number of Engines: 1.
Engine Manufacturer: Teledyne Continental.
Engine Model Number: IO-360-K.
Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally-
opposed, fuel-injected, six-cylinder engine with 360 cu. in. dis-
placement.
Horsepower Rating and Engine Speed: 195 rated BHP at 2600 RPM.
PROPELLER
Propeller Manufacturer: McCauley Accessory Division.
Propeller Model Number: 2A34C203/90DCA-14.
Number of Blades: 2.
Propeller Diameter, Maximum: 76 inches.
Minimum: 74.5 inches.
Propeller Type: Constant speed and hydraulically actuated, with a low
pitch setting of 12.0° and a high pitch setting of 25.1° (30 inch sta-
tion).
FUEL
Approved Fuel Grades (and Colors):
100LL Grade Aviation Fuel (Blue).
100 (Formerly 100/130) Grade Aviation Fuel (Green).
Total Capacity: 52 gallons.
Total Capacity Each Tank: 26 gallons.
Total Usable: 49 gallons.
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NOTES:
1. 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.
3. Wheel base length is G5"
4. Propeller ground clearance is 103/4".
5. Wing area is 1}4 square feet.
6. Minimum tunuuq radius (*pivot point
to outboard wi!lCJ tip) is 27' 5 1/2",
*
PI VOT POi f'~'f
*
PIVOT POINT
1-3
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SECTION 1
GENERAL
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Wuight in Baggage Compartment, Normal Category:
Baggage Area 1 (or passenger on child's seat)-Station 82 to 108:
200 lbs. See note below.
Baggage Area 2 - Station 108 to 142: 50 Ibs. See note below.
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1,11" 1'''''1 :;,01,·, I", ",1" 111,111"" 1.1':1"'1' r n: ItiGHT position
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NOTE
OIL
The maximum combined weight capacity for baggage
areas 1 and 2 is 200 lbs,
Oil C;rad.· (::1"" ,I" ,,111,")
Mil, I, I;IHC ;\ vi .: I" III I : r:l,d(~Straight Mineral Oil: Use to replenish
:;"1'1".1' "'1'11'1'. 111':;1. ;~!) hours and at the first 25-hour oil chang~.
(:lIliI.llIlIl· III 11:;'- u n t.i l a total of 50 hours has accumulated or 011
'" 1I1:;t 11111 ,1.11 '" 11:1.:; stabilized .
Weight in Baggage Compartment, Utility Category: In this category, the
baggage compartment and rear seat must not be occupied.
'i'lw a.i rplane was delivered from the factory with a corro-
sioll preventive aircraft engine oil. This oil should be
drained after the first 25 hours of operation.
Standard Empty Weight, Hawk XP: 15491bs.
Hawk XP II: 1573 Ibs.
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NOTE
STANDARD AIRPLANE WEIGHTS
Maximum Useful Load:
Contincntal Motors Specification MHS-24A, Ashless Dispersant
Oil: This oil must be used after first 50 hours or oil consump-
tion has stabilized.
Recommended Viscosity For Temperature Range:
SAE 50 above 4°C (40°F).
SAE lOW30 or SAE 30 below 4°C (40°F).
Hawk XP:
Hawk XP II:
Normal Category
1001 Ibs.
9771bs.
Utility C_ategory
6511bs.
6271bs.
CABIN AND ENTRY DIMENSIONS
NOTE Detailed dimensions of the cabin interior and entry door openings
are illustrated in Section 6.
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 (if oil filter installed).
BAGGAGE SPACE AND ENTRY DIMENSIONS
Dimensions of the baggage area and baggage door opening are
illustrated in detail in Section 6.
MAXIMUM CERTIFICATED WEIGHTS
SPECIFIC LOADINGS
Takeoff, Normal Category: 2550 Ibs.
Utility Category: 2200 lbs.
Landing, Normal Category: 2550 Ibs.
Utility Category: 2200 lbs.
Wing Loading: 14.7 Ibs./sq. ft.
Power Loading: 13.1 Ibs./hp.
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SECTION 1
GENERAL
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SYMBOLS, ABBREVII\ liONS I\NI> II HMINOLOGY
GENERALAIRSPH 1lIIIlIVIII\lII\(H.Y J\NI> SYMBOLS
KCAS
KIAS
KTAS
VA
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VNO
VNE
Vs
Vs
0
Vx
Vy
1\11()1,::(',1111" ,I, >I ,\11 'I",,.d I:: IlIdl''iI,ted airspeed ~orrected
fIJI' 1",::,1,,,,, ,11,01111::11111111'111,"ITOl' and expres.sed In knots.
1\11.11,:; "IIII,,,d •. <I ",II'::I"'''ct is equal to KTAS In standard
al.lllI'::ldll-14' .i.l, :;4~a l o v ol ,
1\""1.:.1",1"':11,,.,1 Airspeed is the speed shown on the air-
.:1"" '>I II I<IIC'; d,., I' and expressed in knots.
1\"' d:, '1'1"11"Ail'speed is the airspeed expressed in knots
1".,1:11"",I,IJIIli'(listurbed air which is KCAS corrected for
",11,11.11<1<-;llId I,(!lnperature.
1VI:J1I"II\1"I"illl~Speed is the maximum speed at which you
i un.v 1I::t!:IJJI:lliii;control travel.
lVIaxillllllll Flap Extended Speed is the highest speed, J?er-
'ililssl[jTe'with wing flaps in a prescribed extended pos it ion.
Maximum Structural Cruising Speed is the speed that
should not be exceeded except in smooth air, then only
with caution.
Never Exceed Speec! is the speed limit that may not be
exceeded at any time.
Stalling Speed or the mrnirnum __stea~ __flight sP!:led at
which the airplane is controllable.
Stalling Speed or ,the min~IllIIIll steady flig·~l.!_.speed at
which the airplane is controllable In the lu.nd ing conflgu-
ration at the most forward coutor of gr-av itv.
Best Angle-oI-Climb _,§.12~~~, is l.lru speed wit ich re~ults in
the greatest gain of altitude in a /.';1 von liorizon tal distance.
Best Rate-of-Climb Speed is the sp.,()d which results in the
greatest gain in altitude in a given Li mo.
OAT
METEOROLOGICAL TERMiNOLOGY
1-6
Outside Air Temperature is the free air stat.ic tempera-
ture. It is expressed in either degrees CelsIUS (formerly
Centigrade) or degrees Fahrenheit.
MOD!>;!' JU72K
Standard
Tempera-
ture
Pressure
Altitude
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Standard Temperature is 15°C at sea level pressure alti-
tude and decreases by 2°C for each 1000 feet of altitude.
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).
BHP
ENGINE POWER TERMINOLOGY
Brake Horsepower is the power developed by the engine.
RPM
MP
Revolutions Per Minute is engine speed.
Manifold Pressure is a pressure measured in the engine's
induction system and is expressed in inches of mercury
(Hg).
AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMI-
NOLOGY
Demonstrated Crosswind Velocity is the velocity of the
crosswind component for which adequate control of the
airplane during takeoff and landing was actually demon-
strated during certification tests. The value shown is not
considered to be limiting.
Usable Fuel is the fuel available for flight planning.
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) con-
sumed per hour.
Nautical Miles Per Gallon is the distance (in nautical
miles) which can be expected per gallon of fuel consumed
at a specific engine power setting and/ or flight configura-
tion.
£ is acceleration due to gravity.
Demon-
strated
Crosswind
Velocity
Usable
Fuel
Unusable
Fuel
GPH
NMPG
g

SECTION 1
GENERAL
Cl';SSNA
MOl JI';L R172K
WEIGHT AND BALANCE TERMINOLOGY
Reference
Datum
Station
Arm
Moment
Center of
Gravity
(C. G.)
C.G.
Arm
C.G.
Limits
Standard
Empty
Weight
Basic
Empty
Weight
Useful
Load
Gross
(Loaded)
Weight
1-8
Reference l>al.ullI iH :1.11 unu.g inary vertical plane from
which all lIori:t.ollt.al distances are measured for balance
purposes.
Statioll i~;a location along the airplane fuselage given in
tertllSt)f tlw distance from the reference datum.
Arm is I.lIehorizontal distance from the reference datum to
the con tor of g"ravity (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 re-
ducing" the number of digits.)
Center of Gravity is the point at which an airplane,
or equipment, 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 air-
plane. including unusable fuel, full operating" fluids and
full engine oil.
Basic Empty Weight is the standard empty weight plus the
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 air-
plane.
CI':HHNA
M(1)!<;L lU72K
Maximu m
Takeoff
Weight
Maximum
Landing
Weight
Tare
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Maximum Takeoff Weight is the maximum weight ap-
proved for the start of the takeoff run.
Maximum Landing Weight is the maximum weight ap-
proved for the landing touchdown.
Ta~e is the weight of chocks, blocks, stands, etc. used when
~elghing an airplane, and is included in the scale read-
mgs. Tare is deducted from the scale reading to obtain the
actual (net) airplane weight.
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MODEL H172K
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
m;C'J'ION 2
LIMITATIONS
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2-3
CESSNA
MODEL R172K SECTION 2
LIMITATIONS
INTRODUCTION
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 Ad-
ministration. 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. 3A17 as
Cessna Model No. R172K.