Cessna 208B Grand Caravan: Index

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?2

The "ollowing conditions will cause the autopilot to automatically disengage/ • • •

• • •

:lectrical power "ailure "ailure +nternal "light control system "ailure ! loss o" a valid compass signal %H=G "lag& when a mode using heading in"ormation is engaged ith the H=G "lag present the autopilot may (e reengaged in the (asic wings-level mode with any vertical mode 3oll rates in ecess o" 1'< per second ecept when the C* switch is held held depressed Ditch rates in ecess o" ?< per second ecept when the C* (utton is held depressed !ctuating the manual electric trim

DEFINITIONS AND TERMS A#

AUTOPILOT

This autopilot system incorporates electrically-drive electrically-driven n actuators actuator s that "ly the aircra"t (y moving moving the control contr ol sur"aces which are the ailerons, rudder %when optional yaw damper is installed&, elevators and the elevator trim B#

FLIGHT DIRECTOR

The "light director system incorporates a panel-mounted computer that calculates intercept angles and displays displays them to the pilot as pitch and steering s teering recommendations recommendations on the t he light Command Command +ndicator %C+& The recommend re commended ed pitch and steering display serves as a reminder to the pilot as to which way way he should "ly "ly the aircra"t to get ge t the desired results o" his mode selector input The "light "light director may (e used with the autopilot engaged or disengaged +n the latter lat ter case, cas e, the pilot manually "lies the aircra"t to satis"y the command (ar on the C+ which is positioned (y the computer computer rather than than allowi allowing ng the autopilot autopilot to satis"y satis"y the computed computed comman commands ds • •

•

The autopilot can only (e coupled to the t he 7!E 1 receiver The "light director %=& mode must (e selected (e"ore the autopilot engage mode %!D :7G& can (e selected The !E !E+@7+C* D@:3 Q1 switch supplies power to the autopilot and ::E T3+ circuit (rea)ers

THE AUTOPILOT AND FLIGHT DIRECTOR COMPUTER CO MPUTER A#

YAW DAMPER (YD)

+lluminates when the yaw damper %optional& is engaged B#

MODE MODE ANNUN NNUNCI CIA ATORS ORS (FD (FD00 AL ALT0 HDG0 HDG0 NA NA"0 APR   BC) BC)



















?#

+lluminates continuously when the autopilot is coupled to the glide slope signal The GC annunciator will "lash i" the glide slope signal is lost %G* "lag in C=+& The autopilot reverts to pitch hold operation +" a valid glide slope signal returns within ? seconds, the autopilot will automatically recouple in the G* mode +" the valid signal does not return within ? seconds, the autopilot will remain in pitch attitude hold until such time that a valid glide slope returns and the aircra"t passes through the glide slope !t that point, G* couple will re-occur D#

TRIM WARNING LIGHT (TRIM)

+lluminates continuously whenever trim power is not on or the system has not (een pre"light pre"light tested The T3+ T3+ warning light light illumi illuminates nates and an audi(le audi(le warning warning will sound whenever a trim "ault is detected The autotrim system is monitored "or the "ollowing "ailures/ • • •

E#

Trim servo running without a command Trim servo not running when commanded to Trim servo running in the wrong direction

AUTOPILOT (AP) ANNUNCIATOR

+lluminates continuously when the autopilot is engaged lashes 12 times whenever the autopilot is disengaged %an aural alert will sound "or 2 seconds& F#

AUTOPILOT ENGAGE (A (AP ENG) BU BUTTON

hen pushed, engages the autopilot when all logic conditions are met G#

PREFLIGHT TEST (TEST) BU BUTTON

hen momentarily pushed, initiates pre"light test sequence which/ • • • • • •

•

H#

!utomatically turns on all lights Tests Tests the roll and pitch rate monitors Tests the autotrim "ault monitor Chec)s the manual trim drive voltage Tests all autopilot valid and dump logic +" the pre"light is success"ully passed, the !D annunciator light will "lash "or ? seconds %an aural tone will also sound simultaneously with the annunciator "lashes& The autopilot cannot (e engaged until the autopilot pre"light test are success"ully passed

BACK BACK COU COURS RSE E AP APPROA PROACH CH (BC) (BC) MOD MODE E SEL SELEC ECT TOR BUT BUTTO TON N



















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I#

APPROACH (APR) MODE SELECTOR BUTTON

hen pushed, selects !pproach mode This mode provides all angle intercept, automatic (eam capture and trac)ing o" E@3, 37!E or @C signals plus glide slope coupling in case o" an +* The trac)ing gain o" the !D3 is greater than the gain in 7!E 7!E mode The The !D3 !D3 annunciator annunciator will will "lash "lash until the automatic capture sequence is initiated @n the 3emote ode !nnunciator, !D3 !3 will annunciate until the automatic capture sequence is initiated !t (eam capture, !D3 CD= will annunciate #

NA" NA"IGA IGATION ION (NA (NA") MODE ODE SE SELE LECT CTO OR BUTT BUTTO ON

hen pushed, selects 7!E mode This mode provides all angle intercept %with H*+&, automatic (eam capture and trac)ing o" E@3, 37!E or @C The 7!E annunciator will "lash until the automatic capture sequence is initiated @n the 3emote ode !nnunciator, 7!E !3 will annunciate until the automatic capture sequence is initiated !t (eam capture, ca pture, 7!E 7!E CD= will annunciate K#

HEADI EADING NG (HDG) DG) MOD MODE E SEL ELE ECTO CTOR BUT BUTTON

hen pushed, selects the heading mode which commands the aircra"t to turn to and maintain the heading selected (y the heading (ug on the H*+ ! new heading may (e selected at any time and will result in the aircra"t turning to the new heading with a maimum (an) angle o" a(out 20< *electing * electing H=G mode will cancel 7!E, 7!E, !D3 or BC BC trac) modes L#

ALT ALTITUD ITUDE E HOL HOLD D (AL (ALT T) MOD MODE E SEL SELE ECTOR CTOR BUTT BUTTO ON

hen pushed, selects altitude hold mode which commands the aircra"t to maintain the pressure altitude eisting eisting at the moment moment o" selection selection :ngagement :ngagement may (e accomplishe accomplished d in the clim(, cruise or descent +n the !D3 mode, altitude hold will automatically disengage when the glide slope is captured M#

FLIG FLIGHT HT DIRE DIRECT CTOR OR (FD) (FD) MODE MODE SE SELE LECT CTOR OR BUTT BUTTON ON

hen pushed, selects the "light director mode, (ringing the command (ar in view on the !+ and will command wings-level and pitch attitude hold The = must (e selected prior to autopilot engagement N#

"ERTICAL TRIM CONTROL

! spring-loaded-to-center roc)er switch will provide up or down pitch command changes hile in !T, will ad.ust altitude at a rate o" 00 "pm hen not in !T, will ad.ust pitch attitude at a rate o" 0$ deg;sec ill cancel G* couple The aircra"t must pass through the glide glide slope again again to allow G* recouple recouple O

YAW DAMPER SWITCH



















?

hen depressed, allows the pilot to manually control the aircra"t %disengages the pitch and roll servos& without cancellation o" any o" the selected modes ill engage the "light director i" not previously engaged !utomatically synchronises the "light director;autopilot to the pitch attitude present when the C* switch is released released or to the present pressure altitude when in !T hold mode ill cancel G* couple The aircra"t must pass through the glide slope again to allow G* recouple $#

MANU MANUAL AL ELE LECT CTRI RIC C TRIM RIM CONT CONTRO ROL L SW SWIT ITCH CHES ES

The le"t hal" o" the switch provides power to engage the trim servo clutch The right hal" controls the direction o" motion o" the trim servomotor servomotor +n order to operate the electric trim, (oth switches must (e selected simultaneously hen the autopilot is engaged, operation o" the electric trim will automatically disconnect the autopilot R#

AUTO AUTOPI PILO LOT T DISC DISCON ONNE NECT CT+T +TRI RIM M INTER INTERRU RUPT PT (A+P (A+P DISC DISC+T +TRI RIM M INTER INTER)) SWITCH

hen depressed will disengage the autopilot and yaw damper and cancel all operating "light director modes hen depressed and held, will do all a(ove and also interrupt all trim power %stops trim motion&, disengage the autopilot and yaw damper and cancel all operating "light director modes BEFORE TAKEOFF TAKEOFF RELIABILITY TESTS

1

Gyro Gyross -- !llow low # R ' minute nutess "or "or gyro gyross to com comee up up to to spee speed d

2

!E+@7+C* D@:3 1 *witch -- @7

#

D3: D3:+GH +GHT T T:* T:*T T BAT BATT T@7 --- D3: D3:** ** and @B @B*:3 *:3E: a ( c

!ll annunciator li lights on T3+ annunciator annunciator "lashing "lashing !"ter !"ter appro approim imate ately ly  secon seconds, ds, all all annu annunc nciat iator or lig light htss o"" o"" ecept ecept the the !D ligh light, t, which will "lash approimately 12 times and then remain re main o""

+" the T3+ warning light light stays on, the autotrim autotr im did not pass the pre"light pre"light test The autopilot circuit (rea)er should (e pulled !utopilot and manual electric trim will (e inoperative '

an anual :lect lectri ricc Tr Trim -- T:*T as "o "ollows lows// a

(

!ctu !ctuate ate the the le" le"tt sid sidee spli splitt swit switch ch unit unit to to the "or "oree and and a"t a"t pos posit itio ions ns The The tri trim m wheel should not move 3otate the trim wheel manually against the engaged clutch to chec) "or override capa(ility !ctuate the right side split split switch unit unit to the "ore and a"t positions The The trim wheel should not move and normal trim wheel "orce is required to move it



















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

lig light =ire =irect ctor or --- :7G! :7G!G: G: (y pres pressi sing ng the the = = or or C* C* (ut (utto ton n

?

!uto !utopi pilo lott -- :7G! :7G!G: G: (y pres pressi sin ng the the !D :7G :7G (ut (utto ton n

$

lig light ht Contro Controls ls -- @E: @E: "ore, "ore, a"t, a"t, le"t le"t and right right to to veri veri"y "y that that the the autop autopil ilot ot can can (e overpowered

8

!;D =+*C;T =+*C;T3+ 3+ Button Button --- D3:** D3:** Ee Eeri"y ri"y that that the autopi autopilot lot disco disconn nnect ectss and and all all "lig "light ht director modes are cancelled cancelled

9

T3+ -- *:T "or ta)eo""

AUTOPILOT LIMITATIONS •

=uring autopilot operation, a pilot with seat (elt "astened must (e seated in the le"t seat

•

The autopilot and yaw damper must (e @ during ta)eo"" and landing

•

The system is approved "or Cat + +* conditions only -- !pproach ode *elected

•

The autopilot must (e disconnected at 200 "eet !G !G The autopilot must (e @ during use o" stand(y "lap system

•

•

+n accordance with !! recommendation, use o" (asic pitch attitude hold mode is recommended during operation in severe tur(ulence

MA!IMUM ALTITUDE ALTITUDE LOSS DUE TO MALFUNCTION

Cruise, Clim( and =escent aneuvering !pproach

00 "t 100 "t 100 "t

ATTITUDE ATTITUDE INDICATOR INDICATOR COMMAND BAR

=isplays computed steering commands re"erenced to the sym(olic aircra"t The command (ar is visi(le only when the = is selected The command (ar is visi(le only when the = mode is selected The command (ar will (e (iased out o" view whenever the system is invalid or a "light director mode is not selected





















?$

The aircra"t pitch and roll attitude is displayed (y the relationship (etween the "ied sym(olic aircra"t and the movea(le (ac)ground =uring "light director operation, the sym(olic aircra"t is "lown to align it with the command (ar to satis"y the "light director commands

HORIONTAL SITUATION INDICATO I NDICATOR R The H*+ provides a pictorial presentation o" the aircra"t deviation relative relative to E@3 radials or locali6er (eams +t also displays glide slope deviations and gives heading re"erence with respect to magnetic north The gyro is driven electrically NA" FLAG

The "lag is in view when the 7!E receiver signal in inadequate hen a 7!E "lag is present pres ent in the H*+, the autopilot operation is not a""ected a""ected The pilot must monitor the navigation navigation indicator indicator "or a 7!E "lag to ensure that the autopilot and;or "light director are trac)ing valid navigation in"ormation LUBBER LINE

+ndicates aircra"t magnetic heading on the compass card HEADING WARNING WARNING FLAG (HDG)

hen the "lag is in view, heading display is invalid +" a H=G "lag appears and a lateral mode %H=G, 7!E or !DD& is selected, the autopilot will (e disengaged The autopilot may (e reengaged in the (asic wings-level mode along with any vertical mode The C* switch would (e used to manually manually maneuver maneuver the aircra"t laterally laterally COURSE BEARING POINTER

+ndicates the selected E@3 course or locali6er locali6er course on the compass card The selected E@3 radial or locali6er course remains remains set on the compass card when the compass card rotates

TO+FROM FLAG FLA G INDICATOR



















?8

COURSE DE"IATION BAR

The center position o" the omni (earing pointer moves laterally to pictorially indicate the relationship relationship o" the aircra"t to the selected course +t + t indicates degrees o" angular displacemen displacementt "rom E@3 radials or displacement in nautical miles "rom 37!E courses COURSE DE"IATION SCALE

! course deviation (ar displacement o"  dots represents "ull scale %E@3 S 10 degrees, @C S 2O degrees, 37!E S  nm& HEADING BUG

oved (y the heading selector )no( to select the desired heading

SLA"ING AND ACCESSORY AND COMPENSATOR UNIT This unit controls the compass system

MANUAL+AUTOMATIC (FREE+SLA" (FREE+S LA"E) E) COMPASS SLA"E SLA"E SWITCH

*elects either the manual or automatic slaving mode "or the compass system CW+CCW COMPASS MANUAL MA NUAL SLA"E SLA"E SWITCH

ith the switch in the 3:: position, allows manual compass card slaving in cloc)wise or countercloc)wise position The The switch is spring loaded to the center position

SLA"ING METER

+ndicates the di""erence (etween the displayed heading and magnetic heading Ap de"lection



















?9

The "unction selector switch controls application o" power and selects mode o" operating "or transmitti tra nsmitting, ng, testing, and warm-up *witch positions are as "ollows/

B#

OFF

Drimary power is removed "rom the system

SBY

%*tand(y& !"ter #0 seconds in this mode, places the system in operational ready status Ase during warm-up and in-"light periods when the system is not in use The word *TBF is displayed in the lower le"t corner

TST

%Test& %Test& *elects test "unction to determine the operational ready status ! test pattern is displayed 7o transmission is possi(le The word T:*T is displayed in the lower le"t corner

ON

*elects the position "or normal operation Commences Commences radar transmission =e"aults to K mode and 80 nm range K will (e displayed in the lower le"t corner and 80 will (e displayed .ust a(ove the right end o" the top concentric range mar)

ANTENNA TILT CONTROL

The tilt control ad.usts the antenna to move the radar (eam up to 1 degrees a(ove the hori6ontal or to a maimum o" -1 degrees (elow the hori6ontal position The hori6ontal position is indicated indicated as 6ero degrees on the control The tilt angle selected is displayed in the upper right corner o" the indicator C#

STA ST ABILISA LISAT TION (ST (STAB) PUSH SHBU BUT TTON

hen pushed in, sta(ilisation is disa(led The words 4*T!B @5 will "lash on and o"" in the upper le"t corner hen in out position, the antenna sta(ilisation is restored This "eature )eeps the antenna a6imuth parallel parallel to the ground, independent independent o" aircra"t attitude The antenna compensates "or up to L 2< o" aircra"t pitch and roll D#

GAIN CONTROL

Dermits ad.usting the radar receiver gain in the terrain !D mode only +n the test "unction as well as in all weather modes the receiver gain is preset



















$0

intensity Green, yellow, red and magenta agenta area o" storm "lashes (etween magenta and (lac) to indicate strong storm cell G#

W (WEAHER) PU PUSHBUTTON

*elects weather mode when selected  is displayed in the lower le"t corner o" the screen @peration "or the  mode is the same as the ! ecept the areas o" strong rain"all appear as a steady magenta colour and will not "lash (etween magenta and (lac) as it does in ! ! mode SAFETY PRECAUTIONS •

=o not turn t urn on or operate opera te within 1 "eet o" ground personnel or metal o(.ects

•

=o not turn t urn on or operate opera te during re"ueling re"ueling operations

MARGIN OF A"OIDANCE •

!void any cell (y  nm i" the temperature is a(ove "ree6ing and (y 10 nm i" (elow "ree6ing

•

hen penetrating an area o" storms and passing (etween two cells, a minimum corridor o" 10 to 20 nm is required

•

+" the radar return is very intense with hoo)s and scallops, increase this distance accordingly

•

!void (y 10 nm or any cell that is changing shape rapidly

•

7ever "ly under an overhang overhang "rom a mature cumulonim cumulonim(us (us cloud

E!TENDING LIFE OF THE MAGNETRON •

The system is designed so that "ull operation is possi(le #0 seconds a"ter turn on

•

The pilot may choose to leave the "unction switch in @ rather than *BF i" no signi"icant



















$1

AIRSPEED !K+A @D:3!T+7G *D::= %Emo )

1$ +!*

!7@:AE3+7G *D::= %Ea& 8$0 B* $00 B* ?20 B* 000 B*

1'8 +!* 1#$ +!* 12 +!* 112 +!*

!K+A !D :KT:7=:= *D::= %E"e& @< T@ 10< !D* 10< T@ 20< !D* 20< T@ #0< !D*

1$ +!* 10 +!* 12 +!*

ENGINE START START CYCLE A*+7G +7G TH: TH: !+3D!7: B! B!TT:3F

A*+7G :KT:37! D@:3

#0 se secon conds @7 @7 - ?0 se secon conds @ @ # #0 seconds @7 - ?0 seconds @ #0 seconds @7 - #0 -/: @ 20 seconds @7 - 120 seconds @ 20 seconds @7 - 120 seconds @ 20 seconds @7 - ?0 -/: @

POWER PLANT (PT6A'114A) +7+A 7g @3 *T!3T+7G

12 %pre"era(ly 18&

::3G:7CF !+3*T!3T 7g

inimum 10

3+*: +7 +TT !7= 7g @3 *T!3T

aimum 10 seconds





















$2

!K+A C+B

18?

$?

101?

1900

!K+A C3A+*:

18?

$'0

101?

1900

+=:

--- -

?8

2 %+7&

- -- -

!K+A 3:E:3*: U 18?

80

101?

182

T3!7*+:7T UU

2200

80

102?

2090

*T!3T+7G

- -- -

1090

-- --

- - --

!K+A C@7T+7A@A*

18?

80

101?

1900

U UU

3evers erse po power operat eratio ion n is is time limited to < -/ These values are li limited to 2 :=<:

OPERATING ALTITUDES 7@7-+C+7G 7@7-+C+7G C@7=+T+@7* C@7=+T+@7* +C+7G C@7=+T+@7*

2 000 "t 20 000 "t

C@7=+T+@7* +TH !7F +C+7G +C: @7 TH: !+33!:

20 000 "t

WEIGHTS



















$#

!D* =@7

2'g

FUEL LIMITA LI MITATIONS TIONS T@T! A:

22'' l(s

T@T! A7A*!B:

20 l(s

T@T! A*!B:

222' l(s

!K+A +B!!7C:

200 l(s

!K A 3A==:3 *+=:*+D =A3!T+@7 # minutes %due to possi(le "uel starvation&ith low "uel reserves %A: @ annunciator @7&, contin continuou uouss uncoord uncoordin inated ated "lig "light ht with with more more than than one quarter quarter 4(all 4(all55 out o" centre centre positi position on is prohi(ite prohi(ited d Anusa(l Anusa(lee "uel "uel quantity quantity incre increases ases when when more severe severe sides sideslip lip is main maintain tained ed A*: @ !EG!* The use o" avgas is restricted to emergency use and shall not (e used "or more than 10 hours in one overhaul period ! miture o" one part avgas and three parts o" Net !, Net !-1, ND-1 or ND- may (e used "or emergency purposes "or a maimum o" '0 hours per overhaul period !vgas contains tetraethyl lead %T:& to increase its critical temperature and pressure hen mied with .et "uel, the the result is that the lead ends up up stic)ing to the tur(ine (lades (lades and vanes vanes

MINIMUM OIL $UANTITY $UANTITY

Cessna 208B Grand Caravan: Index

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