VANCOUVER ISLAND HELICOPTERS LOGGING

JILIGHT MAl'I'UAL SUPPLE!\1ENT Ka32 -1

to

KAMOV Ka32 All BC FLIGHT MANUAL

for Aircraft

Reg. C-GKHL C-FIGR C-GURI

SIN 31594 88-01/03 31585 87-07/05 (31600) 8810/10

For the Installation of

VANCOUVER ISLAND HELICOPTERS LOGGING EXTERNAL CARGO EQUIPMENT

Approved by P-LSH99-026

This supplement authorizes operation of the aircraft when the EXTERNAL CARGO EQUIPMENT (323.9600.9000,000) and VANCOUVER ISLAND HELICOPTERS LOGGING'S EXTERNAL CARGO EQUIPMENT detailed in Master Document Drawing List VIHL 550-MDL is installed in accordance with LIMITED SUPPLEMENTAL TYPE CERTIFICATE P-LSH99--026.

Sections 1 through 5 of this document comprise the approved Flight Manual Supplement.

Compliance with Section 1 (Limitations) is mandatory.

This supplement must be attached to the basic Flight Manual when the EXTERNAL CARGO EQUIPMENT is installed in accordance with P-LSH99-026

The information contained herein supplements the basic Flight Manual only as applicable in the sections contained herein.

For Limitations Procedures & Perfonnance infonnationnot contained in this supplement, refer to the basic approved Flight Manual.

,.......~ ... ...,._..u-----..---~ CANADA ,

DEPARTMENT OF 't'RANSPORr 1\IRCRAH CER'fiPICATION

PACIFIC HlWlON

AUG 0 4 2000

BY.~~O~D-­mijll'IF!CNrE~. ~IV l :-J:-5\!~q .o]/(,~1!!.~-·-

VANCOUVER ISLAND HELICOPTERS LOGGING

FLIGHT MANUAL SUPPLEMENT Ka32 -1

for EXTERNAL CARGO EQUIPMENT

Table of Contents Section Title

[()'·---General

1.0

2.0

3.0

4.0

5.0

Limitations

Normal Procedures

Emergency & Malfunction Procedures

Performance

Weight & Balance

Summary ofRevisions to T.C.C.A. Approved

Aircraft Flight Manual Supplement for Kamov Ka 32A11BC

Anlendment Date Effective Entered TCCA No. fnserted Pages By Si 1mature I 3-8 2000 Front page F.T.II :\11'i~V

\ f)JM \V(r( '· l u

Page

0-1

1.1--1.2

2.1--2.9

3.1--3.3/3.4

4.1--4.19/4.20

5.1--5.4

TCCA Approval Date

! ~. ·Od 2.- lq'1'1 (\..,. ll1<Ar k 1 f/OV.,)

0

VANCOUVER ISLAND HELICOPTERS LOGGING

FLIGHT MANUAL SUPPLEMENT Ka 32-1

fbr

EXTERNAL CARGO EQUIPMENT

GENERAL

SYSTEM The Ka-32 VIHLoggingHookAccessmy System.

The Logging Hook Accesory System consists of two hooks/grapples suspended from the main Helicopter External Load Hook these hooks/grapples are controlled by a switch on the collective., the switch toggles relays mounted mi the helicopter airfi·ame. The switch toggles eitlter relay, or if a mode selection switch on the main console is in the R.H. position, one or both relays are toggled on or off.

The output from the two relays is fed through a Mil spec connector mounted on the airfi·ame neat' the main cargo hook position. The wirinll is routed fi·om the Mil spec connector to the outside of the aircraft where it is ternunated in a quick release connector. The quick release connector is employed to allow jettison of the lower hooks and their attachment lines without damage in the case of an emergency release.

The main cargo hook system is not changed. The hook catt be opened either by an electrical signal or a manual release operated by a foot pedal in front of tho Pilot.

Circuit Function:

A select switch on the center console allows selection of circuit operation for four difterent accessories that can be controlled from a switch mounted on either collective. When "Hook" is selected the collective switches allow energization of the white mode solenoid or both Hook solenoids. In the same manner if"Grnpple" mode is selected the action of collective switches allow opening or closing of a Grapple by controlling a hydraulic pack.

In Bambi/foam mode a timed release of fire retardant foam or Bambi Bucket water release can be accomplished through collective mounted switches.

The action of the collective 4'witch energizes one relay or the other if in Bambi, foam or Grapple modes. The collecU~~ switches when in Hook mode, will operate either the "white" relay or both relays.

Operation of the controls for NOR!vfAL PROCEDURES and Ei'vlERGENCY and

MALFUNCTION CO:l'{DITIONS are given in sections 2 and 3

TCCA APPROVED P.Ol

r •

r, r

SECTION 1 LIMITATIONS

CONDITIONS OF OPERATlOi'l

Operation of the helicopter with no toad on th~ external cargo suspension hook is

authorized without ·rernovir.g the uolt from helicopter within the buslc RF).! limilatlons .•

QAU'riQi:'l THE GROUND : PERSO:-.;-iEL WILL BE INSTRUCTED THAT BEFORE :STARiTNO THti HELICOPTeR · OPERATIO:-.'S W!TH AN EXTERNAL LOA.O AT HOVER . THE. LOWER· HOOK .OR CABLE ;\[CST TOUCH THE · GROL'ND TO DISCHARGE THE ST.A!lC ELECTRICITY: .

WEIGH'!' LIMITATIONS

Ma;<irnum gJ.:oss w~igh, in.elucling e~<ernol cargo load is 12700 kg (2791J8 [b)

To cnlc.ulure :a flying ;,.·dght for >pecific flight condilk>ns r~f .. fig·~re .j..j oi th¢ present Sup.Pkm~nt; for ~~o~ight cvrr~cticn for humid air rer. n~uri:: 4-1. s~c:jon ~ of th< :Sasic· RFM.

Maximum e:<tcrnul c•rg6 load is ~<Ill!) l.:~ (II023Lb)

AIRSPEED LL'I.IlTATION

With. an external cargo load Vne shall not exce<ld I ~0 km/h (I 02KlAS) or airspeeds indicated by ASI Vne index whichever is less.

In case of the Limit Signal System failur" or with the stntic pr<::;Sur<; selet:tor switch in EMERGENCY position Vne snail be deOned b)' Tabl~ 1-1.

MANEUVERE'G Ll~IIT ATIONS

When -carrying txtemal.carg<;> load the Roll angle is limited tci 20 degrees

FLIGHT CREW U\llTATIONS

Dep~nding on tM. cur go; route and weather conditions the· op~r:Hor. Selects the flight cn:w:

0 2 pi!Q\S

• 2 pilots and operator

1- I

. FLIGHT MANUAL SUPPLEMENT ' • • I, ~ ••

. VIHL-Ka32-l

Vno,.J<.nol$

t JoOo KG (24200 L.B) < WE!OHT :$ 12600 KG (27710 LB)

~ +40 +30 +20 . +10 0 -10 -20 -30 -40 -.SO . . ·0 . 10() 100 100 .. 100 too 100 IOO 100 100 JOO· 2000 . 100 100 100 100 100 100 100 )00 tOO 100

4000 80 90 . 100 toq 100 100 100 100 100 tOO

6000 60 70 80 . 90 100 tOO 100 100 100 100

8000 4C 50 60 .. 70 80 90 too IQO 100 98 10000 30 40 ·so 60 71) 80 90 100 94 J2000 ?0 40 45 60 70 ·80 90

!4000 I 45 I ss 70

'Table)-1. Vne lil'niJS. f~r flight with static rr<ssur~ s~tector switched tO . · EMERGBNCY o( !fllml< s\~nal ;)s:em has 1\\lled

ISSUE I

FLIGIITMANUAL SUPPLEMENT VIHL-Ka32-l

I s E. c T I 0 N 21 . . . I NORMAL PROCEDURES

Flight preparation particulars

Before the flight evaluate the operating . conditions for the external cargo transportation and, taking into account the task, do the following:

Maximum external cargo weight -DEFINE.

Maximum helicopter flying weight with th~ external load • CALCULATE

Required helicopter fueling -CALCULATE

Note· During operati~ith exterimlload the height-velocity limitations may be left out of account. If possible, to avoid entering this zone during hooking, release or after dropping the load at hover, it is reasonable to calculate the helicopter flying weight by the moment of hooking the load according to recommendations of Sections 3 and 4 with account to the cable length and obstacle height (hover height over load hooking or unhooking area).

EXTERIOR CIIECI(

Cable with the lower hook (or without it)­deployed at the pad, if possible to a complete length, at the helicopter left and connected to the upper hook.

External cargo suspension system components (cable or rope, hooks) -UNDAMAGED

TCCAAPPROVED ISSUE 1 2-1

INTERIOR CHECK

Rear view nli.tmrs -ADIDST

Ground specialist (operator, flight mechanic) is positioned by the lower hook -CHECK

LOWER HOOK CHECK Grapple/ Hook Selector Switch - HOOKS

Load release switch on the collective stick -press forward + aft

Load· release switch -RELEASE

Normal operation report from the ground specialist -RECEIVE

Grapple/Hook Selector Switch - GRAPPLE

GraJiple check operation

Grapple normal operation report from the ground specialist • RECEIVE

UPRIDCCHECK

FLIGHT MANUAL SUPPLEMENT Section2

Ground specialist is positioned by the upper lock -CHECK

EMERG RLS button on the cyclic stick - PRESS AND MAlNT AIN PRESSED

EMERG RLS button -RELEASE

Upper hook nonnal operation report from the ground specialist - RECEIVE

UPR I-IT< FROM EMERGENCY RELEASE PEDAL command

Emergency release pedal -PRESS

Pedal -RELEASE UPR HK OPEN light -OFF

Upper Hook normal operation report ll'om ground speCialist - RECEIVE

ROOKING THE LOAD

The load can be hooked after the helicopter landing near the load or at hover.

LOAD HOOKING WITH THE HELICOPTER LANDING AT THE HOOKING PAD The helicopter shall be landing so that the load is in the pilot field of view at a distance enabling the ground persomtel to hook it. After the load is hooked, by the command of the ground persomtel - takeoff and hover over the load

FLIGHT -HOVER switch

Lift the load (see below)

TCCA APPROVED 2.2

-HOVER

ISSUE 1

VlfTIA<a32-l

LOAD HOOKING AT HOVER

On cotmnand from the ground or from the operator hovor over the cargo so that load is in the pilot field of view, on the left. To discharge the static electricity, lower the helicopter until the suspension assembly or the cable (if any) contacts the ground. By a further little descent make the cable slack to allow the ground persotulel to work with the suspension assembly.

LINE POSN FLIGHT- HOVER selector switch -HOVER Lift the load.

LOAD LUlTING

Using the rear-view mirrors and on commands from the operator hover ov.er cargo.

Prelimhtaty cable tension up to (200 ... 600)kgf value according to the load meter- CREATE

On signals fl·om the ground the correct< shackle fastening - VERIFY

On HSI indications the correct hover over the load -CHECK

By a smooth rotor collective pitch increase • separate the load from the ground at a height of 2 ... 3 m(7 ... 10ft).

According to tho load meter indications the load weight - CHECK If the load meter does not register, land and investigate

NOTE When lifting bulky loads on a short sling the load meter indications exceed the real load weight-because of' the main rotor downwash effect on the load.

FLIGHT MANUAL SUPPLE!YllGNT

Load to a height, exceeding the height of obstacles at the acceleration distance by 5 m (17ft). -LIFT

NOTE

If the load starts hunting at hover, by a smooth cyclic stick deflection move the helicopter in the direction of the load deflection and when the HSI pointer approaches zero position­eliminate the helicopter displacement and press·the trim button.

IN FLIGHT OPERATION

FLIGHT -HOVER selector switch- FLIGHT

Helicopter acceleration at engine takeoff rating or near to it - AGGRESIVEL Y APPLY

Cable position without allowing the HSI pointer to go beyond the second division

-CHECK At stabilized speed TRIM button

-PRESS AND RELEASE

NOTE The load hunting in flight is identified by the HSI pointer deviation, load meter indications and appearance of variable loads on controls. To eliminate the load huilting it is necessary to transfer the helicopter to climb or descent. The helicopter transition to descent (if the height allows)at a velticat'speed of2 .. .3 m/s and 100 .. .150 km/h lAS is the most effective method to stop the load hunting. The load hunting in flight can be also eliminated by making a coordinated turn in the direction contraty to the load deflection.

TCCA APPROVED Issue I

VIIIL-Ka32-1

Descent before the deceleration initiation at a speed not exceeding the limits of the Flight Manual, Section 1 and with account to the load behaviour on the hook.

Helicopter deceleration without the load hunting SMOOTHLYPERFOR!vi

CAUTION

AT A SPEED BELOW 50 KMIH lAS (27 KIAS) AND AT VERTICAL DESCENT MAINTAIN TJill VERTICAL RATE OF 3 MIS 590 FTIMIN) MAXIMUM AT AN UNINTENDED VERTICAL RATE INCREASE BEYOND 3 MIS (59 FT/MIN) l'ROCEED AS FOLLOWS o THE VERTICAL RATE IS ABOVE 3 MIS (590FT/MIN) BUT BELOW 4 MIS (800 FTIMIN) - SMOOTHLY INCREASE THE MAIN ROTOR COLLECTIVE PITCH AND SET THE ;YERTICAL RATE AT 3M/S (590 FTIMIN) MAXIMUM. o IF IT IS IMPOSSIBLE TO DECREASE THE VERTICAL RATE FROM 4 MIS (800 FT/MIN) TO 3 MIS (590FT/MIN) BY INCREASING A COLLECTIVE PITCH OR lF 11IE VERTICAL RATE INCREASES BEYOND 4 MIS (800 FTIMIN) - TRANSFER THE HELICOPTER TO ACCELERATION. AT A HAZARD OF Tlffi LOAD TOUCHING THE GROUND OR AN OBSTACLE-RELEASETrillLOAD FR0M THE HOOK. • AT ACHIEVING 'frill 50 KMIH (27 KTS) SPEED - SET UP THE NECESSARY FLYING MODE.

2,3

FLIGHT MANUAL SUPPLEMENT Section2

FLIGHT-HOVER selector switch- HOVER

V81tical cable position according to the HSI indications- MAINTAIN

Helicopter in to the wind -TURN

Hover height over a pad before the load stowage, which must be at least equal to the cable length plus obstacle height increased by 5 .... 10m (17 .. .33 ft.) -CHECK

LOADRELESE

Vertical descent up to 3 ... 2m (10 ... 7 ft.) load height over the pad. - EXECUTE

Load

Load stowage place at 1 0 ... 15 m (33 ... 50 ft) on the left -OBSERVE

TCCA APPROVED 2.4

VIHL-Ka32-l

Smooth load tramfer to the load stowage pad, on the operator and ground personal commands - EXECUTE

At a maximum 0.5 m/s (91ft/min) vertical rate the load on the pad - PLACE

Cable -SLACKEN

To release lower hooks press switch on collective forward for both hooks, release and aft for single hook release.

Taking the helicopter to the right the load release process -MONITOR

By the LWR HK OPEN light illumination - CONTROL THE LOAD RELEASE

MODE SELECTION SWITCH PLACARDS

1'1 A T E

,{" 0

t. SEE FIG. 2.8

ISSUE

0 R A p p

1 E

H 0 0 ]{

s

!•'LIGHT MANUAL SUPPLEMENT

SECI'ION.1

Pilot HSI

Load meter ll\dleator EmtrQenoy load 11IIUI

pedal

EM~G RLS ~oad relun

Colleetlvll pitch control lever Cycla control stlok

:· .. .

Instrument board

contra! pedutal

§ §

OPE."t"CR PI OT

( HOVER J

External lo11d sy$\t~m a_el•otor $WI\chea pencl

Figure 2·1. E.lt~molload system controls, monitoring ~nd W(Ulling ~lement5

ISS\.:"E I 2-SIH

FLIGHT MANUAL SUPPLEMENT

Section 2

LD\1ER HOOK SYSTEM VIH LOGGING HOOK + ACESSDRY Sv/ITCH HOOK· SIN~LE.;

GRAPPL(JCLOSE I BUCKET/fOAH

VIHL-Ko.32-1

EXTERNAL LOAD 1'-----"--.-r-h EMERGENCY

RELEASE BUTTON ( FACTORY SYSTEM)

""'=:---,:;r--1-L--t-'

LANDING LIGHT SELECTOR S\11TCH

LANDING LIGHT CONTROL <FACTORY )

TOP VIE\o/ OF COLLECTVE CONTROL LEVER

FIGURE 2.2

ISSUE 1 2.7

FLIGHT MANUAL SUPPLEMENT Section .t

GRAPPLE MODE

VIHL-Ka32-1

CYCLIC I'ITCH C:Or«l\OL STICK

1. Bxtemalload lllumtnotlon U~t ~ontrol but· . ton (rf>lmt<i,)

~.Autopilot Emor)!eney 1:llsen~:avement button 3, WhUI_ ·ar-uko ·c<mttollover

4. Resotved .button

5. 'l'rfm ccntrolbutton

6, Communlq.tlon button ~wltoh P·SIO ·radio . . 7.llxtemallond. drop trlg~ot (r~erved)

COLI.I!;C'rlV& PITCH CONTH·O~-l.&YitR

l.llxternnl-lond ~mergtMy drop button (rt$ervod}

2. Landin~ llyht $elcetor $Witch

3. Lnndllly lluht ~ontrcl button

4. Limit $Witch c'ut.:ln~ 'Jut atndpllot uitltude Sl\11101

5. Trigger o( frlclion cnul)llllll

6. lnleurut4d ni11ht $;.'$t~nl mode Nl~ctor swllch

7, Flouts ln!lntlon button (rostn·ed)

(fWD -OPENS GRAPPLE AFT-CLOSES GRAPPLE

FIGURE 2.3 Controltmlts arranged on the collective pitch contt•ollevet· and cyclic conti·ol

ISSUEl 2.8

FLIGHT-MANUAL SUPPLEMENT Section 2

TCCA APPROVED ISSUE I

:: ' ., .

VIHL-Ka32-1

PAGE2.9

llT.TOf.l'T' r t. r -P•.mNT VIHLKa32-1

!SECTION 3 I EMERGENCY AND MALFUNCTION PROCEDURES-

EMERGENCY LOAD lUCLEASE

External load must be released in the following case~:

• at tho hover and vertical descent for load stowage if the maximum engine power is used and it is impossible to set the necessmy vmtiea[ descent speed (the main rotor RPM drops below 85%)

• when the crew loses the visual contact with the ground in the snow (dust) storm conditions.

• at a hawrd of a load contact with ground or obstacle at the moment of acceleration or deceleration.

• when the load hunting endangering the flight safety is impossible to eliminate

• at a forced landing when it is impossible to land with cargo

• at both engine failure

• at one engine failure if horizontal flight OBI with extemalload is impossible.

• in other cases (}ndangering the flight safety upon the pilot decision.

The emergency load release fi·om the hook is made by pressing the EMBRG RLS button on the collective pitch lever or by pushing the mechanical load release pedal.

TCCA APPROVED 3.1 ISSUE 1

NORMAL AND EMERGENCY LOAD RELEASE SYSTEM FAILURES

NORMAL LOAD RELEASE SYSTEM l1AILURE (LOWER HOOKS)

Indications: At pressing the hook release switch on the collective forward the hooks do not release.

Opeti the guard on the collective and press the BMBRG RLS button

El\1ERGENCY J,OAD RELEASE ELECTRICAL SYSTEM FAILURE

Indications: At prossing BMBRG RLS button on collective the upper hook does not release.

Procedure:

Press the EMERGENCY load release pedal.

Confirm load has released visually.

FLIGHT MANUAL SUPPLEMENT VIHL-Ka32-1

SECTION3. ENGINE FAILURE WHEN CARRYING EXTERNAI4 CARGO LOAD Load from the external sling

-RELEASE in emergency mode. NOTE

If the engine fuilure has occurred at a forward speed assuring the flight without desCQnt, effect the load release in a safe place before the landing approach on conuuand from the flight director.

At the engine failure during the load hooking (or release) at hover or in clin1b (descent) phase witl1out forward speed -act according to the preliminary evaluation ofthe opcratil1g conditions over the pad.

It is reeonuneuded at tllis evaluation, to account for the hellcopter safe flying weight assuring tl1e landing or one engine flight after releasing tl1e load with tlte millinuuu required fuel reserve.

TI1e safe flying weight detennilted by fig. 4.2 ru1d 4.3 (sheets 1,2) cha1ts after the load release, ensi1res position of the hcllcopter below the AVOID zone and that determined by fig. 4.3 (sheets 3, 4,5) charts e1isures its position above this zone.

In view of the above, tl1e following procednre is recommended;

At the engine failnre in a 10 .. 30 m(33 . .100 ft) height range over tltelanding pad under tho helicopter (the helicopter weight is determined by the fig. 4.2 data) proceed as follows

Main rotor collective pitch to maintain the rotor RPM 88% mililinum

-REDUCE BY (2,5)' Descending helicopter in to tl1e zone free of people and cmgo -TRANSFER

Rotor collective pitch at the 5 .. 3m(l7 .. 10Ft) -INCREASE aggressively to maximum TCCA APPROVED

Collective pitch lever after the Jandiltg -FULL DOWN to Ute stop

Brake trigger on the cyclic stick -PRESS

Engines -SHUTDOWN

Helicopter - DEENERGJZB

At the engine fhilure in a 10 . .120 m (33 .. .400 ft) height rru1ge over t11o obstacle to transfer to OBI flight (the helicopter weight is determined by fig. 4.3 data) proceed as follows:

Helicopter in the acceleration with a pitch angle up to milms 15" -TRANSFER

Rotor RPM~85% by a (2 ... 3)' rotor collective pitch reducing -MAINTAIN

In tllis case the engilte must attam t11e takeoff (or maxintum2.5 minute) rating.

2.5 MIN PWR LIMIT LIGHf- ON probably

Helicopte1· speed and height during tlw acceleration - CONTROL

Helicopter acceleration after achieving a 50 .. 60 km/h (27 .. 32 kta) speed • CONTINUE i11 horizontal flight or with a smooth climb

Helicopter after acllioving a 95 km/h (51 kts) speed - TRANSFER in clilnb

Best flight speed -SET

Further actions in tlte flight -proceed as in the case of one engine failure.

LIMIT SIGNAL SYSTEM FAJLURE Indications: Airspeed wanling indicator flag -IN SIGHT

Procedure: Rcfcl' to Tablel-1, Section I, RFM for V., !units. Flight

ISSUE 1, 3-2

FLIGHI' MANUAL SUPPLEMENT

VOln'EX-RlNG STATE

WARNING

THE VORTEX-RING STATE MAY ARISE WHEN THE DESCENT VERTICAL RATE OF 4 MIS (800FT/MIN) IS EXCEEDED AT SPEEDS BELOW 50 KMIH IAS (27 IGAS)

Indications:

Indicated airspeed -below 50 km/h IAS (27 KIAS)

Vertical rate- exceeds 4mls (800ft/min) and does not diminish at the rotor collective pitch increasing, but increases on the contrary.

Sharp reduction of helicopter controllability.

Shaking, helicopter roll, pitch and yaw oscillating motion, blade vibration.

TCCA APPROVED

Procedure:

Load fi·om the hook -RELEASE

Rotor collective pitch by 1/3 -REDUCE energeticaUy

At the smne time, as far as tho height allows, by an energetic cyclic stick forward movement - ATTAIN a helicopter nose down pitch angle up to 20"

After helicopter shaking, oscillations, blade vibrations stop (2 .. 3 s approximately after pushing tl1e cyclic stick) - RECOVER the helicopter from the dive.

Rotor collective pitch -INCREASE

Speed more than 50 km/h IAS (27 IGAS) -SET

Fmther actions - according to the situation.

ISSUE 1 3-3/3-4

INTRODUCTION

No change from basic Flight Manual pect'ormanco with no load attached tQ cargo hook.

NOTE

Petformancc may be affected by the size and shape of the external load.

HOVER CEILING

Hover ceiling graph (fig. 4.1) shows the max weight for OGE hover for all barometric heights and outside air temperatures (OAT) with AIS ON and OFF.

TCCA APPROVED

VIHL-Ka32-1

LANDING OEI AFTER LOAD RELEASE

The helicopter maximum flying weight OEI assuring a safe landing from hover after load release depending on the barometric height and outside air temperature (OAT) is presented on the respective charts (fig.4.2 of this Supplement).

TRANSITION FROM HOVER TO FORWARD FLIGHT OEI AFrER LOAD REI,EASE

The maximum flying weight for safe transition fi·om hover to forward flight OEI after load release depending on the barometric height and OAT is presented on the respective charts (fig. 4.3 of this Supplement).

ISSUE 1 4.1

·.··:.

1 > I ' I

PFU~$$URE: ALTITUDE, · ~ ..

1 I I I I l I 1 t 1 I I_!_ I I. _t I I I I I I I I '

...L 'riiiA. 1-'- ' 1 I ; I I I i I I I 1_1 1 1 I I 1 , I I I I.J.I_Ll_

I I I I tJo. ....... """\ j.,.J I

. ' I ' ! I I I ll,_l.~

' : MAX 'miGHT

' ' I I l_l..l

I , .. .... ,,

... -... ..,._,. I· l_l

I

. '

I 1 I _l

I ' l I I

_] I. • ' I

I·· :-·1--1· J.·.):. ·to·· ~p ...

lil I· ·I I I I ' '·

I I· I I

' ' I I • I I I I- I !:-'

·I 1 I .J. 1- \..I- . f_i·-)·,

I·

:·.

·I •I I 'I·' I I I· I 0-','. :·.·

I . I I I

I _L

I ' ' I •, I

' ' ' ' I

.. ,.,. I !

::1. .I· I I I , ... I

I· I. lo-

• .. . :·\,. I;' ·:.L:I·:! I •.1 ., " I ....... , .. •. '>;>.- '~. ') I .

.... 1_.-:.-·w-,~-r :~'-~T·.- .:· · -H·I!.;"'·-, l , ... ,._,._'·I

- 1 1- . I ( I -,.

;: I I ,.

_,_·

,I' .l ·,.- I. ,_.

' . ' . ' ·.'

1 1· I·· V. '.'H-:<

\. I -,-. !....:-- : 'I' I I L

1'_1;, I .I. I·

1 ·I I I

1iU!)f\ I

I \Ll. I I . !''

' I I I I I ' I I I I I I .!.. I I ' I_L I I I I

I I. 1 .. 1.- I I I I ' 'I ,.-, -I .. -:-· -- .. "';' !. ' I '· I .. ' I

I .' .. . I .. '. ·· .. I ~0 .. -so. :..o

' I I I

I

I

' .. ·.

' I I I

., ' ' .

' . I I

> I . ' '_l.!..:::! I I I I

I I I

I 1 I I I 1 I I -- - .... - .... - -- -.. MlH 'N::fGHT . ' ' I

· .~ ' : • 1

: .: · · • io . ;:: .. · o ·-w • -~- . - .. ··---

T:!MPE-'<ATVR!:, c. . .

~.J f • 1 I I . 1 '-I I

.......,,. I

"::y: . I I I 1_1 I

I I I , I :

··l '.

1-: I I 1 1 1 I .-....:::____.·

,. I

10

.';,;

5 b -.... <:> El ?.:

••

~ .H-~oeo;

I o

' I

HOVEROG!! TAKEOI'.f' POweR

AJSON 1 • I I

' ,. I I >

PliES SUR!!" A~TmJDe,M

l I 1

I I I I 1 1 I I I

,• o I

' . ··~J ........ , ~

4 ..... • • I j I _,. ~ ......

• - ~ ~ .!., , 1 •I

' ' ' ' ' o ' I

0 I I

'I ' ' 0 I o

I I, 1 I

~WEIOl')T

I. ' . ;.

I I I i

I

~

. ·: ' . ~ . '

. I

' ,.

L--.

.' I

.so

....

I

-50 I

·_,o-. I .

.zo

f19ure 4-L (SM~I Z of 4) Hover co.lling. (METRIC)

' '

. -.. •:

1 r• .> . o

-•o ·.o>. 'toMP!i.'lATURE: •c .

)

I

10

10000

I > I

I I t I

' ' I I I '• 1 I I ! I I

I I \ i'

'

I I I I

I '

I I I 1

' I

... '

• I

I >

•

'

'

HOvEROGE TAIQ;OFF PO'.WR AlS O~F

• ' I • •

I I ' I I I •

I I ' ' '

•

' I ' Ri;S$1-JRfl

tliTODE • e>rr ' .

"I

' '

•

' '

.... L ... L....l ~ I I I '), ..... ----ri· .... (! j MAX 'l.l'iOIOifii

·• _ .. ·:·_·,

.. \:

: ..

l l l ~,,,

. ' ' ' l

t I . ,I . 1•

' .

..... ' '

·' •.

..

I f I I

...... }. "<

I I• t

. ' . .. -.-.: T'.·' I

o> 16 20

' ' !·'

.,

' I ' '

• • :c;'

... ' ' ' I

" I . .,

I ' t I I I

' ' I I I \

. 1 I • I

{ I I

1 ~ 100~ : I 1.\,:•-•'

., . : . '· . "; 6®0 ....__ l \-.

~."::<> irooo ~

. ~· ' I' lQOOO '

,4 S I t

\: t I ..... I t ' , •

:. I : I ;-; 12SOO i " I I .

I • :-. t4'eoe • ' l •

' ' 0 ' I hi I

' . '

' '

'. • . I • I ·•. J ~:· ! . . r • r . l

$Q .io ~ oo TEMPEAATUI'<E, <c - ....

Figurt 4·\·.(Sh~ 3 of 4). !-lover C<ili.tls (IMPERIAL)

-·.;- '; ~~~~~~~i~~i~IJ.~-~~--!1..,_~_;_r; __ 1_,,_'•!_f_l._!_,_t_!_1_~_;_~_!_-~.:_l_1:.:.~.J,,.:_:_.i_!_!_~-~-~,~~~~~$f~*4 ': _ .: _ "~- ~r:r:~~·w1?~t~~-~:;~:: .. _

15000

14000

13000

12000

.. -.. ~:-~:,.;, ,, __ .. :-.-.L .. _ .. , c.-~.t-;-_. ;; .. )_;_~- -r:·.~·~<t---'-.f···' -... :~:; . .: .. .y

. -,,

-:,>r>;· ~.,_c£:_ :~.

k.'.·-,_._ ..

•

WHEEL HEIGHT AllOVE SURFACE 33 FEEl -·. ·. -:. :. -.

s . . , ...•

_., ,.. ,.,_ •! ';;· .. _.,., .. _., !•·X :,;;;. 7-'t J"l!'/.t

-~-- ··." .,_ -.-~ . ' ... ' ·~·- '-'-., .. . ,,.:•.

t·- I ,.... .• . '1 .. 0

' ' ' ."' I . ' I I I

' > .,:..;....!.. • I I ! ''- -:-r'

.... '.· . '

I ' I" I·

~ MIN wh3Hf • ~r:-1- ' -, I I ·,- I 'j..- · 1 · I I

.··.••···· ·. . ··•.. ,. ;.;:~.; .. · teo:;o;' < ... -. ,. .:.:.'· ,.,, ..•.

V.ElGilr, LB

Flsu~ 4:i: (Sh~n ~f 4). (j;;,;~'wc\gh\ ;:.,u;·~ 1~ relweJ io complete sate tanding om · · · . · . ·'to conllll~l'tsii'Jc(iiildini;oEl .· · · . ... ·

· . (1\"'PERIAL).

VlJIL..Kn32-1

f-OAT,'O 1 I I I I I JllLj__I_~IL ~ f-I 'I I I I 1 J I .o:ISOPF ,... ,--I"VI 1 I" I I I I EXreRWL LOAD . f",l I "I I IS REI.EAS~O c- -

").._ M'tll!\ EN GIN!! - -I 1--. I i"-' I"' l I FAILURe I .....;....... .. 30. I !"-.! I :"'-I ~I I ! l ' I I u ;,, I I ~ J •

~ . "-.I I I "N .. , I i i I I ; I \ I ! 'I· I I

' I IN I I ·" I i" i ').,..' I 1_11 .l.l IJ .

i ·"' ""'-1 I .I"\... I IN :-..;_ I I I I I I I I 'I"' I I !i'-, I I I i'< I f'·, ! I I I I I I I I J '"""I I I i'-; I I !""-I ' ........ 1 I I I I l I I I '

l "' r I ' ........ 1 ! !" -;-.. llll!...l..J

: I I ·""' I

l '" ; "'-i I I ! I ' ' i : . I, • ! I I ......... : I . ......, . I . ......, I ' l I

. . \ ' I I I I I .....,. ' " ' i I I I ! : I

' ! ! l ' I·! ........ ' .......... ! ! I I ! : :

' MIHWEIOHT I I ' ' ........... . I "....., I ; ' I I ' . I ·' ' : ......, i I I I ' I I ' I '. ' ' ' I ' ' • I • ' I ' .. I

. . ·.:·; 7000 aooo . ·. 11000 1?000 \vaiom·.Ko . -l A!$ ON -. l!X7'ai\NALLOAO

-IS ReLEASED _,.

I . AFTER ENGINe --

I '""' ......... . FAlLUR~

I i ""'" . ""' CA'i',tC I I

! . : ! ~- ' i ; I : ·~~ +5

! ; ' : : I ! I I • '1 .-·20 : l :

I ' ' : '

f.l{~, !S ... ~ ,._, __ ._

~ ZQoo .-_._. - I ! ! ' -40 I -

I I : ' ;

: .I

; i :

. I

I ---· t_:_:·f:·:A:_={--,; ,-·,:.--__ ._,_ ;,_-~---.

I ..-...--~~-..-.. -----·· __ ,_ ___ ........__,__~.

MmWEIGHT . i.: ' ;

J. .. .. I I 1 I

7000 eooo 10000 . 11o00 . 12000 WE!QHT, KG

· (Sheet 2 of 4), G!ws'W¢igbt v.itb ~xterna!load relens<d to e<>mp!oto.safelru\din&, OEI · (Ml'l'RJC)

4-7

.: . ,, N,"

.. ··.·• !! . : (: ' .. ;/:_ .. ' . v. ;,;, .· ... , ~ r: .;.-.iliL •· · · · · ·

.. ·• . ·.· f.l~Jt, ·: ,·· .,·' .

VIDL-Ka32·1

WHill'.L HEIGHT I>BOY£ SURFACE 98 FEET . ... .

~:

'· """ "'~

= WOHr .. lB

AISOH t;XTER(W. l¢AO IS RE\.V.SE-0 AfT!iR eNOIN~ f MLIJR!

3000

. .: ' ' ! I I I I I 111111111 .t·y~~ I I I I . ·--~-~- . . ·- '.

AJSOFF 1-. tW s I I I I I EXreRNAl. LOA() ·-f-

i"-t" I I ' I I I ISRelEASSO I AFTEll ENGlllE. -I-.J ' I I I iTT

1F1LUR!l 1-'-·--~a .I . ......_,, I 1 I I I I I I l I !

··-·-- I I i' '\.! I r I I . I I I I I I ! I I ' '-' I I i'-' ! I I I I I I ! 1 I I I I 1 ' ,.,. i ~ I ' I '."""-I I I I I 'I I I ! I I I I ' . ·. {13 I I :'.•·· . ,, . ' I I i ,. J I I ' I 1- I I ' . 'i"-1 ! I '.: : ' ·". I I I ; I ! I I ' I I I I "-..· I "'-...: i I i I ' I ' i I I

' : : I !

·An : "-.. I I ; ·"- I I I : I I l : t' I 1 -~

' ! ,. ; : ' I ' ! ! ' ! • l • I . 1000

~ . "-.. ' ' ·'\ . : i I

I I I r I : " . ' ; • : I ;

' ' ....... MJN WoiGH1' ' ' ' : H . . ·;-

' .,_ • I

' ·r . : _o: .. -. l I f I I I' I

;: :, \ )q9o 10000 11000- 12000 _wi!!OHT .1<0

-~~------~------~------------~----~ • I

- -- ,'.

-.; :

, .AlS ON ext!:i'NALLOAO

. IS R!lwt'-SE!;> AFTER ENGINE

.FAILURE

l

~ . I

Figure 4<2. (Shoot 4 of 4) Gross W~igllt "l.th exton\slkilld released· ·. •· to <:Ompleto :$2-fe landlng<JEI - ·

{Mim\10)

. :-.

.. ,,_,

·,---_---.·._·---.· •. --_ ••.. ··_._._ •• __ ----_•_.i·::l··_ •• ~_-_;_._:·.·_--.:~_-::,. __ •• ;.-_:~_~·;,• __ .·_:._:_·.·_.:_._·-·!-, __ ·_·:.·_::_.~,-.: __ ·_-~.,i!_,_: _____ •• __ ; __ ·-.··_-_-_---.:-·~-·_.--·.·--,·--,-_.-,···._-_--_ ' . . - . ·.- -. -: · ·,· ; _; . •_- :: tih~j£\f~~· ~.,~&-:~L~,

4-9

! .. ··•• ' I

I . "'-

·= WI!I<:'JHT, LB ,

_.10). Oross Wcight wl:!> ~ lood teleas<d t6 attAin Ytoss OEI (L\IPERIALl'

VIllL-Kn32-1

WHt:EL HEiGHi ABOvE SURFACE' 10M

11000 12000 WEIGHY.KO

I I

I l

. ·1C>:'.OO. 1100() 1~00()

.WEIGHT. KG

"""'"''"-3, (Sheet 2 or 10) Qro~ Wcll)ht vMh external k>ll<l rol• .. •d to a ttl> In Vto"' Ot!l QJETRlC)

4-ll

...:.··.·.··.·.· •... •,'.•·.·,::.· .• :·-,·~ .• ·•••·.·.·.• .•• ·.·.~·: .. ~.~-·.: •. _: ..•.•. ·.: .•. :_·.;.:,:.~.-.; .•... :·.·.:., .. ;.····: · .• ··. . . . :-_: -~>{~ -·. T, • " , l;r:~:~:~~<t;.:_,.

... ... .

t. ··:}''/''' .

i. ··-' VIHL-Ko32-1 ...... ' .. '

~ ,,,;: .· . ::-:- ~',. ~ ,S < FF

~ "'I.· I!"• ... I"" <· 1'.. •· . ~ I~ ;:+ I'- · ;.1,; ltioi

~ sooo -~ tl ~ : i~··. 7··:·:-!;:~...l· Hl'\.....Pr-....>-HHri+-+---Hr-1--J....W . ;;::. : tw]jl'~: ' ),.. --: I·

1000¢

sooo

-~·'J·:fl.•' . . ,,. ·'·?i'

. '

-~, .

;;(· •if• ·r: '• .\,I ·h •t ' tHT I :·

' '(;, ,. -I ' J . p";

I {·

-k , .. ·.[.

• ~· '

. ' ·· :. IV ....

. . ';,:;, 1:,. .. : >'·'

ifJ'· x: ,; . .. 0 . ~

[· .

WEIGHT,LB 26C(>O

"'' IF ~El . I

Wf IO I I'" r;A.J.: L PA' '

'"'· L ':': l:' :v .

f .

I, '

. .

i . I I

moo 25()00 WF!IGH1', ~B

Weight wlth ~xtemal load released to attain Vtoss OE! (IMPERIAL)

.. ,:_,) ...

·.· ..••.... J .. ~1~.~j~i.], ~: \'·

.. ·. ·. VIHL-Kn32-1

: i .

:~"'II" I! II •! . : <I'M t· ... , "-. · I "-. • i I ; · I : · : I '

...... : ...... I l I • • T ! : -,

····· · ·· . ·,: ·.· llXnl!\NAl.lOAD -c ·c,: :' :.t'L' ·· · · · .. · IS R~SED ~

, . · ; • · , _._ API:rt eNGINii . ' FAJLUR!!

:.·,MIN

. .

4-13

WctGHT.te 25000

.~·.

20000

., ·'Weight with external load reteased to nttnln Vtoss OEl . (IM·: PER:!A!..l

VIRL-Kn3Z..l ., •. :;.··-·r[:•.-,;·:- ~;, .• :.

WH!!El HI!IGHT·ABOVe.~URFACe!aOM

,. '. '~ , . T ' ! ~ ; '

I

9000 I I

10000

. . ' '. : . l :

. J.

i '

I --; ; "I, 'I:

I I

11000 I<COO WlliClHT, KG

·~··... .'•·.· I·; ,'[ ! · -.· ! . AISON -• · !!XTERNA~ LOAO

ir·::_· ' . . · I ' i I . I : 11$ RBLI!ASED .

: •••·· .•. }'·.· ·. :•.: ' '""' : . I . --: AFTI!R ~NGIN~ . fi ',: .+-<1-f'~ ... c-.?,-.Xod-ilr-~-OvA~•~T,'C i FAilURJ;

Ji·f.i;. ~~~~ ; : ~---_ ·. •:.~';; ·.·~ ·.~·,\. -......."-. '- ,/ ·'n ,.......L-1-...!.__,;:.___ ___ ··~-. :.3\•1i'~ 0 >'~ / I -n•·--~--

;• I I -40'!!! I-·---... ~-. >::_ .. ·0WI'+;f-+-..;....,.. ;:-. 1-\-H~----'---'-- ,., __ _ .· . ; . 'K+-'-'---c--·~c----t-1-\- ·-·---,--~ .. • .. ---

·--..... ~.-

! . ...,·· H--·;-·~ :. --i-'++--1---.--·· _;_,_:.,_._ ... .:.. . . ; ; :

·~ ..

. .! ' ·,>· '!' 'o I

I .I i ! .i ' .

I

aooo ' I

W<JO

'l.

I I

10000

--....

.

I I

I 1000. 120 WeiOHT,KO

00

·.·

.·

1"- I

t(! · · • I · ·. ~\i ki [·.·· 0. . <nM I• ~., '(i !jF:.i'7: •·· +,.:-:-. +I:+.-+\-+, ,-\---1-1--J-+-+-+-l--H

('. · .. : . • m:. •· . ·C

''··: : . ..

:·L:;.

·h.d·•.J . F· .. I

. I·· i . . .. . (:• . . ..

h ·1• · .. ·"'" .·r-v· i:c r:. 1 "· v I'·•

.

20000

. . : . . .

. ' .

. · .

WEIGHT, LB 16~~,\V~;l~h't' with externallond l'eleased to attain Vtoss OET

• .•. • . ; .. U.¥g~CR~L) "·••.·, ·c:r·;-: !U>;·.;,. T<l< r m 1

. •"·'··. •.

·-~''"' i·li·l~ ·•.L ·I I i

I I: """-'·I I -..;, · I I!· ·"-'·I ;· ;"I i"' I I

·r..,l!l''-·1•1" I II;· ·.:·'c,•:·"·i'l.·i·i ... •'-..· !i·~ ..1•··1·:·.1 I

I;"-,. : "'-: : ' l ! ; 10~ ~4-~,~;--.~~~----~.,~,,-r~~~~~.~ .. ~.~~~~--~

,· I I,,'""' '' I 1 ' I•:' I I

.· . ~ OAT,'O! T I I

T I 3000

~ ·20 I 0 f.t·

" I~ ·I' ~

1'... .. .....:. ~ 1<1.

T I "Z f •. : I "'· : 1 I ·•~ ·. ..-.....

I II'<..! T"'-i·l .. -........

... r·t··

3000 . --...

.!....... ...

:ll uJ a .,.....-"-g ~

2000

~ . .L ~-·. ·-.·-. ~-. ..... Q.

1000 ,:1-.

I t

t •

WEIGHT .AND BALANCE ....

. . ~R..Q~§ .. W.~*~!JTMID CGCALC!JMTION ·.•

.~; ... ~-_! ,:~::-.:£-::::.n :.-.;:-,~-- .·_-: _.: --.· ·- ,. '- ----;:-- ..... , . To de{(,~rie'ih~ Gcou Weliht and CG fat a . given m!llit are .Within the limlts, proceed as foll~ws;;!+c {id: . .. . · • obtain the aircraft delivered weight and its

moment fr(Joi the W~lsht and Balance Rec­ord in ihe Helicopter Logbook,

• determine the weight and moment.ofop· tio~al equiJ>ment, refer to Table s. t, ·

• det~un~ the Maidr'riuni Gross Weight coil; · .. · · · · ·· ·· .. !

• clet~i~eili~·C;«el-.lai cargo 'weight, and moinent (efe~ to Tai,lu S·2,

• detetmill~th·;q~a'ri.ii~~ffuel required for operation ll!ld its.rnoinent . -. • • . :-;- '; ·--.:.~---~~-:.::, ->.- --.: .

To obtain the CO add all detennioed.oioments . and divide by computed Gross Weight

. .Tab I.e s: 1. EguH~'en(uriits iatile of~odl~n;s.(W.i,;~) - -·. -_ .. - __ '··- ; :·! ·.;: ., _ _-.:,};:_-;.-,:::::.-.-. ·.·

FUSELA.Qri sri\ TlQN soso·· ':.: LONO!TUD!NAL AR.~. 5.05m

Nos. · · · DESCR1FT!ON

!. STAT!ONARYPA.RT I .. Mo\Jnting truss 2 .. · ··.· upp'i!tnook :i ''·~ o~rencerinll: . · · · ·

I · ·• Line I 0 nmers • · 2 • ·; ur~M met~rs > ;· 3 · 1>1~!ti'pvrpose lin~ 4 . Lo\v~rhook · s · Ner.· ·

.. . ·., . '·

WEIGHT kg

35 II i9

5.0S

MOMEl"T, kgrn

177 S6 96

,_,.. .:·~' .: ~. . . . - . -, ·, - .. ·' . . ·. :·:-. ·- . ..

J'USELAOBSTATiON.l99 in

LONGiTUDINAL /;h'M 199 in -. '. .. .. , ····' --··

Nos. ' DESCRIPTrON WBl(}H'f, LONGITUDINAL MOMENT,. ·lb . ARM,m r •. ··u;.i;i ..

I. STA;TlONARY PART .-... . . I Mo~~tli1gitruss .. 77>' ,;·.·.·199•·. .. •· '<·15323· •·. 2 Uppe'r llookir ·.·· 24.2. ···'{;~.< ···• 4sts.a 3

• • --~ >:,_<•·'"·-.-•• j,' :. ...

41:8 83ts.i ' Defence·trtlig" .

11. REMOV ABLB PART 1 z 3 4 5

Line I o roofers ss . 199 •. 1094S . Line 20 riieters 92.4 199 8387.6. Multi purjlose line 105.6 199 ~lg14,4 .. , Lower hook 46.2 199 9193.8 Net '50.6 199 1001i9.4

.... ·. . ' mlJ:E. .•. . . . . . " . . .. ... . ..... ·1. During extornnl cargo transportation the. cnrgo· c<>tnRartment cover plute neur

Fninies No.J·\I!!d No.9 from below Is dlsussemb!ed, Weight ofdlsasseOJbled c·ovcJ' plate portion ls ~kg (ll.OZ Lb).· . •· : L , · . : . . . · . ·, . ..· · •· · . . .·'

2. Curgo pick-up devices ore dove! oped by, Koinov ~mji':iny, th~{ ore not ~tondcird ·. ·. ~quli>tltilhf'~'i'id~~re ~tve~'lieretili'liii.' e'X\im'Pi~t>:O • i'i;;'. . ., .. ; ,n. '· . .

3. Load liloier,l@§titlotis, t~f~t·t9 .oarg6\v~l?U,J :9\'i~f~~!~<? .P.i,<;jc:uiJ devices w~lghts; · .• ·-· ... .-- - . - - : _,_, ____ ,_ ' --., .... - - -. . .. •-

·. Table 5·2; Bxternill earg~.i~~d!ng inble (Metric). . · .. ,, ... -- ·- .....

FUSELAOESTATlON'S050.

LONGITUDINAL ARM 5.05 M

CAROO WiliOHT. MOM!!N'f CAlWOWoiOIIT · ·. MOMTWI' kg k~m kg kgnl ·

10 ,:50.50 100 ,:, . 50S zo fot 200 .. 1010 30 . !51.50 300 · ,;,.;(ISIS.

. 1~ H~.~o . 1~~ · ·· · ;;;:' mr · ~~ ···~;glo · ~~~· s, 1,m~ RO . :404 ROO . · .;,.4040 : 90 4$4.50 900 ; ':. 4545 .

CAROO WBIOIIT kg

1000. 2000 3000

. ' .· 4000,' · ... sooo;. ·.·,

MOMEN'l' kwn •·.

5050 ... 10100

• lSiSO.

·. ·j~~~~:.· ..

.. .

.. :-._

to~o--~-~~5~o~s--~---~l<~lo~o--~~s=o~5o~··--~----~~~~·~~~·

..... .- ' '

FUSE!AJOS STAT'JOI" 199 in

LONGITUPINAL ARM 199 in

Load v.relgl!t, Moment, Load w~ight, Moment, lb

2':1.\ 4i4 6.1D. 8'E

HO 1:;2 154 173 200 22:0

STA Q

REFERENCE 'OAT1JM•

lb·in S64,4 728.8' 1093.2 1457.6· 1822

!186.4 mo.~ I 2915.2 ' • 3279.6 l 36+4

~ '.-M _ . :. _ "t tn

~ ' :1! ~· .£ ~ .[, ··~· ·~ ~ .t .

Ib

220 440 660 880 . 1100 mo 15~0

1780 2000 2200

lb•in 3644 12S8 1o9n 14576 18220 21864 ·25508 29!52 32796 36440

STA cmiD

;! ~"' .0 ..

.; d d d z :;:;:;: ;!;

I.! .l!'" ..; . u. . u.. u.

. Load weight, lb

2200 44oO 6600 8800 1 !000

~ -d :z: ...: u.

Fig. 5· I. External Slight System Artangement

Moment, . lb·in

36440 72880 IQ93ZO 145760 1sizoo

FLIGHT MANUAL SUPPLEMENT VIHL-Ka32-1

LONGITUDINAL COORDINATE OF EXTERNAL LOAD CENTRE OF MASS.

The Station of the external load centre of mass is defined by the suspension assembly mounting place on the helicopter (see fig. 5.2).

DATA ENTRY INTO THE LilVIITING SIGNAL SYSTEM PROCEDURE AT THE FLIGHT PREPARATION AND AT EXTERNAL LOAD TRANSPORTATION

NOTE

The Limiting Signal System operation principles are presented in the basic Flight Manual (Section 5 and Manufacturer's Data).

The sample for computing at the following conditions:

The flight to the load collection place is made without cargo on board.

The external load is hooked without engine shut-down.

TCCA APPROVED

The formula for the takeoff (flying) weight computing:

Wto = W oq.kg + 0 · 8 (V fuol.to .. l)

Equipped helicopter weight 7326 kg.

Fuel quantity of board 1500 I

Takeoff weight calculation before the takeoff:

Wto = 7236 kg + 0.8 (1500) kg= 8436 kg

Fuel quantity and helicopter takeoff weight selector switches set accordingly in the positions:

Wfuolto- in position 1.6 Wto -in position 8.5

Further actions in the flight:

• When lifting the external load the load reading is 4000 kg

• Transfer helicopter flying weight selector switch in the position 8.5+4.0= 12.5

• After the load release return selector switch from the position 12.5 to the position 8. 5.

ISSUE 1 5-4

Transport Canada Transports Canada

Department of Transport

Suppfementa{ tType Certificate

This approval is issued to:

VIH Aerospace Inc.

1962 Canso Road

North Saanich, British Columbia

Canada V8L 5V5

Responsible Office:

Aircraft/Engine Type or Model:

Registration/Serial No.:

Num6er: P-LSH99-026

Issue No.:

Approval Date:

Issue Date:

Pacific

KAMOV Ka-32A11BC

3 February 26, 1999

March 27,2014

C-FIGR/87-07 /05, C-FMKV I (31599)8809/09, C-GKHL/88-01/03, GURI/8810/10

Canadian Type Certificate or Equivalent: H-100 (KAMOV Ka-32A11BC)

Description of Type Design Change: Installation of External Cargo Equipment

Installation/Operating Data, Required Equipment and Limitations: Installation of External Cargo Equipment in accordance with Vancouver Island Helicopters Master Drawing List VIHL 500-MDL, Revision 1, dated February 25,1999. This installation consists of a dual long lines, a weighing system, a TIL Model TFM-138 FM transceiver and a Narco 10 emergency locator transmitter.

Basis of Certification as defined in the applicable Type Certificate Data Sheets.

Required Equipment: DoT approved Vancouver Island Helicopters Logging Flight Manual Supplement Ka32-1, dated August 4, 2000.

Conditions: This approval is only applicable to the type/model of aeronautical product specified therein . Prior to incorporating this modification, the installer shall establish that the interrelationship between this change and any other modification(s) incorporated will not adversely affect the airworthiness of the modified product.

~~ - Hej~ong~

For Minister of Transport

Canada