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• Luis Carlos Chibuque

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• Ingeniería Aeroespacial

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-

..! '. "1

~

Cr:SSNA

OF CON'!"!:

T.'\BLF:

MODEL TunE

,

TABLE OF.COí~TENTS

,/ ,.-.l-1

SECTIO¡ GENERAL

:,3/

.

•

•

.

•

LlMITATIONS

1

t-JI,

EMERGENCY

L~I

NORMAL

,

PROCEDURES.

.

.:.,:~¡

PROCEDURES.....

4 .

. ....

•.......

:'¡;

5

...... 6

AIRPLANE & SYSTEMS DESCRIPTlONS

i

I

3

WflGHT & BAll\NCE/ EQUIPMU'-IT LlST

I

1

2

PERFORMANCE

'1

.•

. .......... 7

AIRPLANE HANDLING, SERVICE & MAINTENANCE

-

;s;: ':i:.

SUPPL EMENT~,

(Option"1ll'-Systems

'""l'>~.

Description

, & Op~erating P~dur,es).';'

":k 1 ~.::~:

"-"';",.

..~.

~.;..,

. ..' l.;•.

./

.:

. ";0,«..

"~.o'

~:#.'';-

T~ nandbook .•..•.. ill be kept curren! Q)' Servíce letlers pubtished by Cessna ,.1.ircr;¡f: COmprsand lo ¡hose who subscriol? lhrough lhe Owner FoJJow-Up System. t! you are nO! receí .•.ing su~)scr¡prion se:'.'íce, ¡-ou ....•• ill \'~anl lO keep in rouch wit.h yeur C'25sna Deate: ior inforrn'')I:' •

iii/(jv

b!;!:

--,

PllOT'S OPERATING HANDBOOK ~

Cessna.

HAWK XP

•,

1978 MODEL R172K Serial No.

R J!l2- 2, 2 38

Registration No.

1t155QQ

[0

THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR PART 3

COPYRIGHT 1977

Cessna Aircraft Company Wichita, Kansas USA

D1110-13

j

11 I

OONGRATIJtA

TIONS

CESSNA MODEL R172K

CONGRATUlATIONS

••••

wP.loo_ lO th~ raM,kiof Ce5sna o"'Me,.! YO",' Ce,m. has !leeM designecl aru;l COM5l"~e!edlOgive you lhe moit In perfo.mM.;e, ~ono"'Y ,aMdcomlort. 111$ 0"1' de';re ,h.1 YOlU wil! findllyÜ'1gIt, eh"er lo' bua'e 'offeroo by mast Ce""" Oelll"l$: I •

itlf C1!5SNII'WAIIlRAN11l', whlm proVide'CQv.;r.s" forpans ano labor, ¡,avallableat C~'Ma Ocal.m woridwicle. Specllk benefil5 .M pro.iiiom 01 ",arr_Ml)',"tUi oth", limportv"r t~e vent openi~g and . apply suction; a sound: Ir-om.the .warnihg.born will confirm sys~em operahon. .. . Wing 'Pie.Down .- DISCONNECT. . ,

,

1l.

i1 ' 1:

c

@LEFTw,~~1 1.

Trailing Edge_ c AjJer~n •••CHECK heedo;;'

BEFORE JThRTlNG .

1. 2. 3. 4. 5.

I

I

of movement

and security ..•

ENGINE

Preflight Inspectionc -- COMPLETE. Seats. Beits. Shoulder HarnesSeS •• ADJUST and LOCK. FueI Shut'olf Valve .- ON (push fúll in). Fuel Selettor Valve _. BOTH.. " . A vionics fower Switch. AutopiJot (if installed). Electrical c ment .: OFF. . .' ,

Equip.

I

~UTION The avioniics power switch must be OFF during engine start td pr1event possible damage 10 avionics.

I 4-6 , .. --0

:j::';L:TIUf\;

l...;,t;0::'"1 ~ i".~

6. 7. 8.

Brakes. - TEST and SET.. Cowl Flap .- OPEN (move leller inboard reposition), Circuit Breakers -- CHECK fN.

STARTING

4-

NORMALPROCEDURES

MODEL RI72K

. out of locking

hole lO

ENGINE

2. 3. 4.

Mixture - - RICH. PropeHer -- HIGH RPM. Throttle -- CLOSED. Master Switch -- ON.

5.

Auxiliary

6.

Throttle _. ADVANCE lo o"btain 8-10 OJ6H fuel flow then return to CLOSED posítion. Auxiliary Fuel Pump Switch -. OFF. Propeller Ar'ea .' CLEAR. .. Ignition Switch -~ START (release to BOTH when engine starts).

L

7.

8. 9.

Fue] Pum9

.'

Switch

.

~~}ÍIGH.~

NOTE The engine should sta.rt in two to three revolutions. If it does Det continue running. start again at step 3 above. If lhe engine does not start.,leave the auxiliary fuel pum-p switch off. set lhe mixture lo idl~ cut~off.open the throttle. and crank i..mtilthe engine fires (or for"approximately 15 seconds). If sUll tinsuccessful, start again using the nor~ mal starting p'rocedure a.lter allowing lhe"starter motor lo eool.

.ji

10. 11.

t ., ~

J

,

.

., J "

i'"

Throttle .. 800 to 1000 RPM. Oil Pressure .. CHECK.

BEFORE TAKEOFF 1.

Parking

2. 3. 4. 5. 6. 7.

Cabin Doors .. CLOSED and LOCKED. V Flight Control s .. FREE and CORRECT . Flight Instrumen.ts .- SET. Fuel Selector Valve .. BOTH. Elevator and Rudder Trim _. SET . Throttle~OO RPM. . a. Magnetos .. CHECK (R?M drop should not exceed 150 RPM on either magneto or 50 RPM differential between mc¥gnetos).

Brake ~- SET.

~

I

il

,,

4-1

r SECTlON q : : NORMA.-I.,Pi'l:OqEDURES

"

CESSNA MODEL Rl72K

b.

8. 9.

lO. 11. 12.

Pcopeller .. CYCLE from high to low RPM; return lo high RPM (full in). c. E~gine Instruments and Amineter __CHECK. d. SJction Gage _. CHECK (4.6 to 5.4 In. Hg.). AVion:icSI¡POwer Switch -- ON. Radio~ -- SET.

.

AutopÍlot (if installed) -- OFF. Flashi'ng Beacon. Navigation Lights •.nd! or Strobe Lights __ON as required.1 Throttie Friction Lock -- ADJUST,

,TAKEOFF NORMAL

I

TA.KE¡OFF ;

1.

Wing ~la~s -- 0° - 100 (lOo preferred).

2. 3. 4. 5.

Power ¡. F;ULL THROTTLE and 2600 RPM. Mixture --' LEAN lor tield elevation per luel fiow plaeard. Elevator Gontrol •• LIFT NOSE WHEEL at 55 KIAS. Climb Speed " 75.85 KIAS. '

,

SHORT FIELD TA.KEOFF

,

1. 2, 3. 4. 5. 6.

Wing Fiap" '. lO •• Brakes '.• ÁPPLY. . Power -:-FpLL THROTTLE and 2600 RPM. , Mixture - - 'LEAN'for tield elevation per fuel flow plaeard. Brakes RELEASE. , , Elevator Control -. MAINTAIN SLIGHTLY TAIL.LOW ATTI. TUDE. I I "'.',,' , ,7. CJimb Spe~d .• 60 WAS (until al! obstaeles are eleared). 8. Wing Flap¡_. HET, ACT alter obstaeie.s are eleared.

f.

L.

ENROUTE CJIMB

"

"

NORMALCLlMB 1. Airspeed "'7é-95 KIJ).S., 2. Power --'FULL THROTTLE and 2600 RPM. 3. Fuel Selector Valve .- BOTH. 4. Mixture._ LEAN lar altitude per fuel fiow placard. 5. Cowl Flap -' OPEN as required . . '.,.,.

4-8

--....•

SECTION 4 "NORMAL' PROCE:OURES

5. 6. 7,

CESSNA MOOEL

I

R172K

Touchdo"'nI .. •MAl N WHEELS FIRST, ~. Landing F}oll -- LOWER NOS E WHEEL GENTL y.. Braking MINIMUM REQUIRED.

.¡

SHORT

FIElD

llANDING

I

j.

L 2. ....•..3. 4. 5. 6. 7.

Airspeed 65.75 KIAS (flaps UP). . Wing Flaps •. FULL DOWN (below 85 KIAS) . Airspeed MAINTAIN 63 KIAS. Elevator and Rudder Trim -- ADJUST. Power .. REDUCE TO IDLE as obstaele is eleared. Touehdowh _. MAIN WHEE'LS FIRST. Brakes .. APPLY HEAVILY. Wing RETRACT f.or maxÚnum brake eff~ctiveness.

1-

Fla1s --

8.

BAlKED L

LANDING Power.-

I

FIULL THROTTLE and 2600 RPM. .. RETRACT

to 20c.

2.

Wing Flaps

3. 4. 5.

AirspeefI .:.. 55 KIAS. Wing Flaps .. RETRACT slowly after reaching Cowl Flap .. OPEN.

65 KIAS.

AFTER LANOING .'.

I

1. 2.

. .. .

Wing Flaps -- RETRACT. Cowl Flap -- OPEN.

SEGURING tlRPLANE 1. 2. 3. 4. 5. 6. 7.

'.J!...

4-10

Parking Brake -- SET. Avionics P:ower Switch, Autopilot (if instal1ed), EJectrical ment.- OFF. Throllle -- ,IDLE. Mixture -- ¡OLE CUT-OFF (pulJ full out). Ignition S,¥itch -. OFF. Master Switch ,. OFF. Control Lotk .- lNS:fALL. . Fuel Selector Va.lvelL RIGHT.

Equip.

~.

CESSNA

SECT10N

MODEL Rl72K

AMPLlFIED STARTING

'j

'NORMALPROCEDUHE,

PROCEDURES

ENGINE

Proper fuel management and throttle adjustments are ihe determining faclors in securing an easy start from your contip.uous-flow fuel-injection engine. The procedure outlined in this secUoo: should be followed- closely as it is efrective under nearly all operating condUioos. Conventional full rich mixture and h.igh"RPM prop€dler settings an used far st?_rting; the throttle,"however, should be fully closed initially. When ready lo 'Slart, place the auxiliary fue! pump switch in lhe HIGL position and advance the throttle lo oblain 8-10 gal/hr fuel flow. Then c1os•. the throttle and turn offthe auxiliary iuel pump. Place the ignition switcf: in the START position. While cranking,"slowlJt advance ihe throttle unti .. the engine starts. Slow throttle advancement i~esser..tial since the engin( will start readily when the correet fuell air ratio is obtained. When th;: engine has started, reset the throttle to the desired idl~ speed (800-1001: RPM),

.

The eontinuous.flow fuel injection system will-injeet atomized fuel ir the intake pprts as soon as thethrottle and mixture controIs are opened an(. the auxiliary fueI pump i5 turned on. If the auxiliary .pump i5 turned or, aceidentally while tha engine i5 stopped, ,"vith .the' throttle 9pen and the mixture rich •. solid fueI will colleet temporarily in the cylinder intakt ports, the qua-i1tity depending on the amount of thethrottle opening and lh..: length C?f tímethe pump' has been Oper.ating. Ir tbis happens, i t i5 advisablf to wait a few minutes until thisfuel drains away.before starting the eng_~ne To avoid flooding. turo tbe auxiliary fue! pump switch off promptly whe,; the fuel flow reaches 10 gallhr during preparation for engine start.

Engine mis-starts ch;araeterized by weak. ih-termitten t firing followe(~ by puffs oi bIack srnoke from the exhaust are caused by overpriming Ol" flooding. This situation is mOre apt to develop in hot weather. ar when th(engine is hoto Ti it oecurs. repeat the starting routine with the throttl>::: approximately 1/2 apeno the mixture in idle cut-off and the auxiliary iue:

pump switch off. As the engine fires. move the mixture control to fuH riel-. and decrease the throttle to idIe.

•

Engine mis-starts

characterized

~\Vay from the starter.but exeessively lean .mixture

by sufficient power to take the engi nt dying in.3 to 5 revolutiens are the result of ar: áfter the start and can occur in warm al" caJe!

temperatures. Repeat the sta.rting procedure but a.llow additiona} primin; time with the auxiliary fuel pump switch en HIGH before cranking j: Started. Ir extremeJy not temperatures have eatlsed vapor \vhich prevents ¡

"

SECTION NORMAL

4: I PROCEDURES

I

CESSNi\ MODEL Hin!,

I

. [

4f .:

J

"4

~:1

.le-, USE UP AILERON

~ff~ON

LH \VING AND

.

~

~jiitJ~ &t ;o '¡M;I¥%{4iv~~'i.ry;Y_I NElITI'A

L ELEV

A

TOR

~/#' USE UP AILERON ",",~ON RH VlING ANO

~11

~"

At1w\,

in}

.",..:_,_:.;

L.=,:~ .•,.;,'~"",=,~"~:~"E",~',,':',,lI,?:,',;., ,.,', ',~."R:,'«",.""A,L,",:L:!,:",:,,":, ',~,_,:,'"":',L",~":,",'~','''',¡,:,~,~,,,,

,J't ••• 11>0•••• lfl

125

g.250 1-

:c

'"

o .J 1-

--:1_. i --.

150

-:t

10

15

LOAD MOMENT/l00D Une reprl!senting

20

25

::n~-::30

(POUNO-INCHESI

odjustable scats shows thc pilot or passcngcr center ef grBv'ity on t1djuslabtc

seats positoned:'or an average occupant. .Reter to forward and ah Iimit:.. 01 occupant C.G. (ange.

the

LOilding Arrangemcnts Oiagram for

Figure 6-6. Loading Gr".ph

-

-50

25

H- - - +- - 1-. ¡~-..¡o-

w

;:

o

-----r --r

-,

100

:c -~••_.,.•.•.••

M._•.

_

q~(_;~ •.~••

LOAoeD

600

. 2S00

700 l.

AIRPLANE

800

MOMENT/looo

900

IKILOGRAM,

1000

MILlIMETEAS¡

1100 1

1200

1300

:": :~'~"'~IM=E/:IHflJ(:1EflfE~~~iJ-'J!I, '.:' ,i:,~"': 2Soo '.

CENTER OF GRAVITY MOMENT ENVELOPE

:

2400

¡;¡

-1 ' --:i: ' -:, --

Q

1-

Z

::>

_

1400

,'.1:"'150 NORMAL CATEGOAY

_

-r-ll00

2300

Q

~.

2200

CJ ' w

~ ~

-

'

::

2100,.

'"_"

,+-

:¡:

'.. ' ''t. -

..J

'";¡ Q

w

2000 1900

-

-O~+

-

T

:,::,~"

'"

,

O

•

"

- -

1800

" --

r-

-

, , ,,: ~:}

- -

1700

4.

.H-

",:.,

" 't, 55

,

UD

65

"

70

-

ti- ~-

-r~ -

-

" lro~+'"r' ""E-I-+

-j- -

rr

:,-21= tj::

-

75

80

LOADED AIRPLANE

",

-

"", e5

90

_

l=t"

,.1

_

- --

-r:-

900

1:: __".

ro

ro

-

100

105

110

MOMENTlJOOO iPOUNO,lNCHESI

Fi.r~l.rn~ n-7. Centm' r,f Gr;'lvi~vI'vlnl1lcnt

Envelone

S

;: o

850

,--'.

.. __ : _ ".

"

w Z

;¡

_1+ . -I~"_ I"r -. - Jt, - -

r:. ., F : .. "" : ..

"'1.

95

950

-- ":

p-

:r:1: .. --1-" :,: -~:t:j:''1' :I--:r'.

',1i!1

-.-.--,

-- ::' ..""':

-

'~++_ "r'~

., -1+ 'TT

,el w

-'-

--

-:\~-J G. G04-A G07-A GI3-A G 1 6-.A __ Glq-A • G22"S __ - .- -G-2"5-S" r .'. G25-S-2 o .•..

025-0 G31-A

l.

G55-A G58-A G6 7- A G8 A-A

? .0 ~~z

~nnK. TOW 1 IN!TALLEO. AR~ SHChNl(NOT 0500228 FAC lOR y IN51ALlEOJ RINGS. AIRPLANE HOI STlNG 0541115 CORROSION PROCFING, INTERNAL SJA.T ICO-I-SC.HHGER I.Ns-TATLATrON Cm-OF TOI STAglLIlER A8RA!IC~ 8CCTS ---0500U41 -1O.W-8AP.-I-HOWEO-1 05010lq PA"lNT SCHEME, OVERALL EXTERIOR IACRYllCJ 0504036 OVERhLL eA SE WHI TE WASH ETCH PRIMER STR I PE COLCR SCHEME PAINT SCHEME',CVERALL EX~OR (MOOIFIEO 0504036 POLY-URETHAt-.E.l . OVERALL BASE l/HITE WA SH PR l ME . COLOR STRIPE SCHEME PAINT. OVERALL ExtERIOR (MODIFIEO POLY0504036 URéTHANE-,.USED wl TH I NTER'AL CORROSICN. PROOFING, I1E~ G13-AI CA~LES. CORROSION RESISTANT CONTROL (NET 050Je36 CHANGE 1 '. .. FIRE EXTINGUISHER, HAND HELD 0501011 STEPS ANO HANOLE,REFUELING 0513415 RUDDER PEOAL OTENSIONS RE~CVA8LE - SET 0701046 OF 2 I STOWABLE - I NS ALLEO ARH SHGWNl WINTERIZATlON KI'T.INSTALLATlON, ENGINE 0501007-1 EOl 0552132 BREATHER TunE INSULATION COVER 1552012

0.5

g-~8r8~~-

11.B*

10.8 0.4 0.6 12.H 11. 6 0.4

0.7 12.7 0.0 3.0 1.7 2.3

~m~mn: ~~gfg~t amm AVIONICS

229.0

Z \0'0> >-J~

t":P 1• I . _.4S. L_ _ t"'---1'0-.0 77.0 (J);p 0.4 __ 1!.3.2_ -=1-'7 ---2-:7 1.6

f

H._

HO 1- A

'1J:r:-

4LXILIARY.EOUIPHE~T

1. o0.4 0.4 0.4

2J6. o Q5.0 91.6'" QC.5 90.5 1 t3.;;» , Cmt'ii1

,

,

.... -

_

ITEM

H07-A-' 2

HI1-A-I

':111-1\-2

H1I-A-3

1-111-A-4

,;

'.~~

LOOP ANTE~NA INSTALLATICN , RECEIVER MOUNT, IdRES AND DMF. IN$TAl,LI\T1CN. NARCO RECEIVEP. fDIolE-190) MOUNTtNG ROX

ANTENNA

H01-"-1

r

:e __

••• ~.

EQUIPMENT L1ST DESCRIPTION

NO

HJ '.- A

'

RH ORAWING

MI SC lTEI;

25 .•0. 27.8 7.0 b.2.4 68.2 13 .0 -

..

J. HAWK -)'P

CH-O

J04-A

-" Iv

OPTlON

PACKAGE~

CONSI STS OF lTEMS HEATEO PITOT SYSTEH COLRTE SY lIGHTS C~l-A NA V .1IGHT DE TECTDRS C40-A FLASHING BEACON L1GHT C43-A 7RUE AIRSPEEO INO. (NET CHA~GEl COI-O STA1IC AIR. AlTERNATE SOURCE DO 4- A DUAL. CON TI'OL S Ee5-A l-2'¿-A-l NAV/CON 385A VOR/lCC "28-1-1 EMERGENC V LOCA 7ER TRANSHITTER NAV-PAC INS1ALLATION (A~AILABLE XP III "Ol-A 300 AOF (R-546-El

J01-A

O>

SPECIAl

J

•

1 1 EOLlPNENT

0500511 0422355-T 0521101 0701013 0506003-3 0513279 0501017 0506005 3910151-35 0470419 3910159

i 6 ~ 3'

45.2.

.1,.9

184.2 18.1 1 S. 5 12.4 . 29.9 116.6

0.6 0.5 N EGL 2.1 O. 1 0.2

-2

16. 1 1.8 21. l' 7.0

24.4 61.0

- -

18. ) ...

21.0

~ MCl

D:t c::>-.l

::a~ ~td[f)

M~t'l

Z;¡,Q _ "Zo-oz >-.l

enM

>el-o>

ITEM NO.

i

EQUIPMENT L1ST DESCRIPTION

V

REf ORAWING

WT LBS

ARM INS

- -

--

Hé-A-l

Jl0-A J 13-A

Jl5-A

!OC TRANSPONOER (RT-359AI t-:2~-A 30C NA Y/COM 2NO UN! T FLOATPlANE FUSELACE SThc TURA L MOOI F I CAT ION S & F1TTINCS FLOHPL ANE COkLOECK y 6RACE ([ NSTALLEOI CSTOWEOI FLOATPL ANE Al L eRON-RUOOER_I ~TERCGNNEG-T----fLOATPLANE ONL-Y-"" ([NSTALLEOI

3910127-11 0500044-41 0513003 0500012

(B~~~~~

J27-A

J30- A-l

UEHSJ_IO_ A--&-'-J-I-3-A-M"E Al SC O F C-R LANOPLANe OPERATIONS MOOEL 246-¡¡4C FLOATS & ATTACHMENTS EDC-24e NET CHANGE BETI.EEN STANOARO LANOI NG GEAR IITEM NOS. BOI-R; B04-R¡ 610-S ANO 6RAKE& NOSE- WHEEL STEER NG SYSTEMSl ANO HOATPLANE KIT (¡ TEM NO, J30-A-11 IS APPROXIHATELY 235 L6S AT ¡

(!:?l ,

:

'"

Figure

7-1.

FÜghl

Control and "Trim Systems

(Sheet

2 of 2)'

7.5'-,;;>

r

1

2

3

5

6

12

13

14

19

20

21

22

23

14

25

l

26

"J

~.

.,

.,¡.,

__

.. _Cb

_

S'

f

"o~

i

3iQM,Qi&M "

I

Alb

a;e"

a e

ttJUJiQ&i¡

¡.......

-.'''!''"~''''-'""""",

,

-

.

1

"

sO

I. 2. 3.

~

UQ

..•roe

..,

f.o

!j In

~

" ¡:;

;3

ro

~ ~ "l1

"

~ ro ~ ~

(JJ.

"."

~'

ro o

-

!:9 ,j

...,

.:,

Cylindor Head Tcmperature Gage and Ammeter Oil Temperatura and Oil Pl'cssUl'a Gaga Left Tank and Right Tank }i'ucl Quantity

4. 5. 6. 7.

~ndicatol'S

Suction Gage Over.Voltage Warning Light Clock Manifold Pressure/Fuel Flow Indicator"

8. 9. 10. 11. 12, 13, 14, 15, 16, 17, 18, 19, 20, 21. 22, 23, 24.

.Flight Instrument Gi'oup Airplane Registration Number Tnchonieter . Encoding Altüneter ADF Bearing Indieator Omni CO\.lrse Indicato.rs . Magnet1c Compass Marl{er Beaco~icator Lights and Switehes Rei.\l' View

Mil"l'Ol'

Audio Control Panel Radios Au topilo! Control Unit Tra.nsponder Secondary AlLimeler Aclditional ¡nstrument Space ADF Radio Flight Hour Recorder

ot.";

25, 26. 27. 28. 29. 30. 3I. 32, 33. 34.

Adctitional

Radio

Spaco

Map Compartment C~\bin.I-Ieat and Air Control Knobs Cigar Ligh ter Wing Flap Switch

and

Position Indicator Mixture Con tr01 Knob Propeller Control !{nob Throttle (Witl1 Friction Lock) Static Pressul'e Alternate SOllrce Valve Instrument and Radio Dial Lighl

Rheoslats

35,

Microphone 36. Cowl Flap.Control Lever 37, Rudder Tl'ini Control Lever 38, Fuel Selector Valve Ha.ndle 39. Elevator Trim Control Wheel 40, Electrical Switches 41. Cil'cui t Bl'eal{crs 42, Parking Brai{e Handle ~ ~3, Avionics PO\NCr Switch 4 '1. Auxilia.ry Fuel Pump Switch 'J5, Ignition Switch 'lG. Master Switch ji?~ Auxiliary Mike Jack ~8. Phone Jack 'lS!.

Prilner

50.

Fuel Shutoff Control Knob

O'JJ

(JJ

~Z

-::~

~0 --,""

00 ZZ (JJ...,

II

"

SECTION 7 AIHPLP;}'JE

¡ 'A

SrSTEMSVDESCRIPTlONS

CESSNA MODEL Rl72K

.

stlff~ners. ceJ?ter. left, ~nd nght.wrap~around skm panels. ~nd formed leading edge 'skiins. The horizontal stabilizer a150 contains the elevator trim tab actua:to~. Construction oC the elevator consisls oí formed leading edge skins, a f9rV¡rard spar. aft cha.nnel, ribs, torque tube and bellcrank, left upper and lo",!er '(V" type corrugaled skins, and righl upper and lower "V" type corrugat~d skins incorporating a tra.i.ling edge cut-out for tbe trim tab. The eleva~orltrim tab CODsists oí aspar, ribo and upper and lower "V" type corrugatéd skins, The leadíng edge of both left and right elevator típs incorporate extehsions which .contain balance weights. . ¡

FLlGHT

COi'lJTROlS

The aírpl~ners f1ight control 'syslem conventional aileron. rudder, and elevator surfaces are fnahually operated through control wheel fer the ailerons and elevator. the rudder. !

(see figure 7-1) consísts 01 control surfaces. The control mechanical linkage using a and rudder/brake. pedals for

. Extensions are available for the rudder/brake pedals. They consist of a rudder pedal fa.ce) two Spacers and two spring clips. 'To instal1 an extension. place the ¡clip on the '1?ottom oC the extension under the bottom oí lhe rudder pedal and snap the top -clip over the lop of the rudder pedal. Check that lbe extension is finnly. in place. To remove the extensions. reverse lhe aboye procedures! I

TRIM SYSTEMS

I

I I

..

."

.

Manually-operated rudder and elevator trim syste~s are provided. Rudder trimmingl isaccomplished Ihrough a..bungee con.oecled to the rudder control s'ystem and a. trim lever, mounted OIi-thecontrol pedestal. Rudder trirnming ~s a.ccomplished by lifting lhe trim lever .uP to clear a detento then rnqvi.hg it eilher 1eft or right to lhe desired trim position. Moving lhe tritn lever to' the right will tri m' .the a.irplane nese-right;' cODversely. mO\ririg ths lever to the left will trim the airplane nose~Jeft. Elevator trimrriing is accomplisbed through the ~levator trim tab by Ulílizing the vertically mounted trim control wheel. Forward rotation of the trim wheel \~ill :trim nose-1own; conversely, aft rotation will trim nose~ up_

l'

u.

,

I

l.

INSTRUMENf

PANEL

.

. The instrum'ent panel (see figure 7-2) is designed around the basic "T'. co~_!.iguration_ The gyros are located irnmediately in front oC the pilot, and ,.

7-8

I I

...;.

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1 i

CESSNA MODEL RI72j,

AlRPLANE

& SYSTEMS

SECTlON 7 DESCRIPTIONS

arranged vertical1y ayer the control column. The airspeed indicaior and altimeter are loeated to tbe !cft ar:d right oC the gyros respectively. The remainder

oí thc f1ight instrurnents

are localed

around

tbe basic

"T".

Engine instruments and ~uel quantity indica:tors are Dear the 1eft edgé and lower portian of the instrument panel. Avionics equipment is staeked approximately on the centerline of the panel, with (he righl side of (he panel containing space for additional iDstnunents and avionics equip. mento A subpanel under the primary instnunenl panel contams the fu el shutoff valve knob. primer, master switch •. auxiliary fu el pump and ignition

switch es. circuit

breakers.

avionics

power switch,

and electrical

switches on tbe leH side, witb tbe engine controls,light intens"ity control s, and alternate 5tatic air conlrol in the center, over the conlrol pedestal. The right side oí lbe subpanel contains tbe wing flap switch lever and position indicator.

cabin heat and air controls, cigar lighter. and map comparlment,

Apedestal, installed below lha subpanel, contains the elevator trim control wheel and indicator, microphooe brackét, cowl flap control lever. and rudder tri m controllever. A fuel selectorvalve handle i5 loeated al lbe base oCthe pedestaL A parking brake handle is mounted below (he subpanel in front of the piloto Fordetails concerning the ínstruments, ~vitches. circuit breakers. and controls 00 this panel, referin this sectioo to~he descríption of the sy~s lo which these items are related.

GROUNDCONTROL Effective ground cootrol whi1e.laxiing is accomplished lhrough nose wheel steering by using the rudder pedals; left rudder pedal to steer 1eft and right rudder pedal to steer right. When a rudde.r pedal is depressed. a spring-loaded steering bungee .(which is connected to the nase gear and to

the rudder ba.rs) will turn the nose wheel through an are oí approximately 10° each side of center. By applying either 1eft or r.igbt brake~ the degree oí turn may be increased. up to 30° each side

of -ceriter.

Moving lhe airplane by hand is mosteasi1y accomplished by atta.ching a tow bar lo lhe nose gear s~rut. If a tow bar lS.i10~available, or pushing.is required. use the wing struts as push poin15, Do not use the vertical or horizontal surfaces lo move the airplaD.e. If the. a;ítpla.ne ís to be towed by vehicle. never turn tbe nose whee1 more t::han 30° eitber

structural

side oí center

or

damage lO the nose ~ear could result.

The mínimum turnin.g radius" of the airplane, using differentlal . braking and n6se \•.. ~heel steering during tax.i, i5 approxirnately 27 feet 5 and 1/2 inehes. To obtain a minímum radius tUTn during ground handling, th~ airplane may be rotated around either rnain landing gear by pressing down

.3ECTJON 7 ;\'IRPLAN8

'&

CF:SSNA

SYSTEMS DESCRIPTIONS

MODEL RI72K

I , ,

on a tailcone bulkhead just fúrward _ Di the horizontal • • -1 ncse wheeI off the g,round. .'.

stabilizer

to raise lhe _ .

"

[1

I

WING FLAP SrSTEr6I The wing flaps ¡tre of the single-slot type (see figure 7.3). and are extended or retracteq by positioning the wing flap switch lever on lhe instrument panel to tbe desired flap deflection position. The switch lever is ;moved up or down in la slotted panel that provides mechanical stops at the 10° and 20° positions\ Far flap settings greater than 100, move the swit~h 'ever to the right to dIear the stop and position it as aesired. A seale and ointer on the left sidb of the switch lever indieates flap travel in degrees .. he wing flap systeJl"i circuit is protected by a 15-ampere circuit breaker, abeled FLAP. on the Ileft side of lbe instrument panel. .

¡

I

1. 11 ¡

i i

NDING GEAiR SYSTEM The landing gearik of the trieyele type with a steerabIe nose wheel,'two ain wheels, and wh~el fairings. Shock absorption is provided by the bular spring-steel I'liain landing gear strJ..lts and the a.ir/oil nos e gear

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Figure 7-3. Wing Flap System

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-.-..__rO HII~!;SS (P'ull d_n'o tl;hlfnt

(PllOn

SEAT SHOWN)

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! SHOULDER

HAItNESS

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7-19

!I AfRPLANE

control knobs below the engine contro;s, labeled PANEL LT and RADIO . : '-. ~ ..

1

7,30

i

,

I

\.

,

SECTlON

CESSNA MODEL RI72K.

7

AIRPLA,,'E & SYSTEMS DESCRIPTIONS

LT, control intensity of the instrument and control panellighling. A slidetype switch (i! installed) on the overhead eonsole. labeJed PANEL LIGHTS. is used to seleet flood l\¡,hting in the FLOOD position. post lighting in the POST position. or a combination ofpost-and Oocd lighting in the BOTH position. Instrument and control panel nood 1ight~g consists oí a single red flood Jight in the forward par! of the overhe~ eonsole. 1'0 use the flood Jighting.rotate lbe PANEL LT rheostat control knob eloekwise to the desired intensity. ' The instrument

panel

may be equipped

'iiV.ith post.lights

whic~

are

mounted al the edge Di each instrument or control and pro vide direct lighting. The Jights are operated by plaeing the PANEL LIGHTS selector switch in the POST"pasitian and adjusting light inteosity with the PANEL LT rheostat control knob. By plaeing tbe PANEL LIGHTS selector switch in the 80TH position. the post lights can be-used in combina~ion with the standard

!laod lighling.

The engine instrument equipment, and magnetic

cluster compass

(ir post lighting is installed). radio have integral lighting and operate

independent1y of post or Hood ligbting. Light intensity of the engine instrument cluster and radio lighting is con.trolled by the RAIJ+e-.LT rheostat controi k.flob. The integral compass-light intensity is controlled by the PANEL LT rheostat control knoh. . A cabin dome_light •.in the a.ft part of lhe o~erh-ead console.

i5 operated

.by a switch near the 1ight._Totúrn the light oo. move the switch to lhe right. A control wheel map light fs available aod is mounted 00 the bottom of the pilot's control wheel. The iight il1uminates the lo\ver portion oí the cabin jusUorward oí the pilot and i5 helpful when checking maps and oilier flight data during -night operations. To aperate the light, first tum on the NA V LT switch; theÍ1adjust th~-map light's intensity with the knurled disk type rheostat controllocated at the bottom of the control wheel. A doo"rpost map light, located

00

the left fonvard doorpost. contains

both red a.nd white bulbs and may be positioned to illurninate a.ny area. desired by lhe piloto The light is controlled by a switch, below the light,

which is labeled RED, OFF. and WHITE. Placing the switch in the top _position wiU provide a. red light. In the bottom position. standard white lighting

is provided.

In the center position.

the map light is turned !Jf!'

-The most probable cause of a light failuré however. in lhe event any of lhe lightÚlg systems

is a burned out bulb; faU to iHuminate when

tUrned on, check the appropriate circuit breaker. If the circuit breaker apened (white bullon popped out). and there is no ohvious indlcation

"

has of a ,

7-31

,

I

I

SECTlON c.;..lRPLAN£

I I

7

.

& ~Y'TEMS

•

1

CESSNA MODEL RI72K

DESCRI?TlONS

short ClrCUlt (~mokf or Odor). turn off the llght switch oi the affect.ed llghts. reset the breaker:. and tUI"n the SWHchon agá.in. II the breaker opens again; do not reset it. ' .

,1 •

,t

I

I

CABIN HEATING, VENTllATING ANO

DEFROSTING

SYSTEM

.

The temperalLrJ and volume ol airflow inlo the cabín can be regulaled to anY,degree desiréd by manipulalion of lhe pusb.pul! CABIN HT and . CABIN. AIR conl~OllknObS (see figure 7.8).

:

I

.

Fo;' cabín verililation. pjl the CABIN AIR knob out. To raise the air temperature. puJ] th~ CABIN HT knob out approximalely 1/4 lo 1/2 inch far a small amount dr cabin heat. Additiona.l heat is available by pulling the knob out farthbr; hIaximum heat i5 available with the CABIN HT l{nob pulled out and lhe 'CABIN AIR knob pushed fu 11in. When no heat isdesired in the c",bin. the CABIN HT knob is pushed lul! ín. . Front cabín hjat lnd ventilaling air is supplied by oullet hales spaced across a cabin manifÓld just forward el the-pilot's and copilot's feel Rear' abin heat and air is supplied by two ducts irom the manifold. one xtending down e~ch ISide" oC the cabin to an outlet at the front doorpost at oor level. Windsh~elddefrosl air is supplied by lwo ductsleading from lhe abin manifold to outlets near the lower edge ol lhe windshíeld. Separate adjuJtaJle ventilators supply addítional air; one near each pper corner ol the .wlndshield supplies air lar the pilot and copilot, and wo ventilators are avallableforthe rearcabin area to supply airto the rear eal passengers. I I

ITOT-STATlt l

,

~YSTEM ANO INSTRUMENTS

The Pítot-statíc sJstem supplíes 'ram aír pressure to the airspeed dicator and static pressure to tbe airspeed indicátor. rate~of.climb dicator and altimetet; The system is composed of either an unheated ar ated pitot tube mou!nted on tbe )awer surface ol the left wing. two. ternal sta tic port~qn the )ower. 1eft and right sides al .lhe forward selage, and tbe assoCiated plumbing necessary to connect the instruents to tbe sources.

l

I

. . .

.

The heated pitat sys em consists of a heatiog element in the pitol tube. rocker.-type .switcll Jitbeled.PITOT HT on (he lower left side ol, the trument panel. a 5~arAp circiJ"itbreaker on lhe switch and control panel. '~

'

.

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L;t.:~.:it;;\¡ A

MODEL Il172K

dl

AIRPLANE

&

SECTlON 7

'1" STEiVIS DESCRIPTIONS

EXHAUST MUFFLER SHROUD

FRONT CABIN A[R OUTLE:T

HEATER YALVE

DEfROSTER OUTLET (2)

VENTlLATING AlR DOOR

CAB[N HSAT

CABIN AIR CONTROL

CONTROL

~''''---REAR

CAB