EASA APPROVED

FLIGHT MANUAL

F eurocopterU an EADs correanv

FLIGHT MANUAL

EC 15581SUPPLEMENT

SAND FILTERS INSTALLATION

I M P O R T A N T N O T E

The in fo rmat ion conta ined here in supp lements o r supersedes the in fo rmat ion g iveni n t h e b a s i c f l i g h t m a n u a l a n d / o r s u p p l e m e n t s l i s t e d i n s u p p l e m e n t 0 .The e f fec t i v i t y o f the supp lement a t the la tes t rev is ion is spec i f ied on the L is t o fE f fec t i ve Pages.

T H I S S U P P L E M E N T M U S T B E I N C L U D E D I N T H E F L I G H T M A N U A L W H E N T H EEQUIPMENT MENTIONED ABOVE IS INSTALLED ON THE A IRCRAFT .

E U R O C O P T E R D i r e c t l o n T e c h n i q u e S u p p o r tA6roport internatlonal Marseil le-Provence 13725 Marignane Cedex - France

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LIST OF APPROVED EFFECTIVE PAGES

EASA CERTIFICATION(1) Page Revision Code

R: Revised, to be replacedN: New, to be inserted

FLIGHT MANUAL

N

suP.1g.P504-20 Page 1

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SUPPLEMENT PAGE DATE ( 1 ) SUPPLEMENT PAGE DATE ( 1 )

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P1 1P5 1

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1 01 11 21 31 41 51 61 71 81 920

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o4-2004-2004-2004-20o4-2004-2004-2004-2004-2004-2004-2004-2004-20a4-2004-20o4-2004-2004-2004-2004-20

LIST OF THE I-ATEST NORMALAPPROVED REVISIONS

NORMAL REVISION : 0D A T E : 0 8 1 0 7 1 2 0 0 4

Approved by DGAC on 08/0712004according to the article 10.3 ofthe CE 1592/2002 regulation

No. Date I No. Date

04-20

EC 155 B

FLIGHT MANUAL

GENERALThe sand filters installation is designed to prevent the ingress ol sand into the enginesin order to avoid premature wear of turbine blades.

The sand filters assembly comprises:- a set of removable MGB cowlings complete with filter housing, interchangeable

with the standard MGB cowlings.- a set of removable fairings placed over the standard removable engine cowlings.- a P2 circuit, feeding the sand exhaust nozzles and provided with an electrically

actuated valve.- a system that automatically closes the P2 circuit valve of either engine in the

event of an engine failure(if N1 of remaining engine exceed max OEI continuousrating).

1.1 PILOT'S CONTROLS AND INDICATORS

OVERHEAD PANEL CAD

cgo)(o

qlnu)

o14

=

P2 Valve closedFilters inactive

P2 Valve OPENFilters active

P2 Valve inintermediate position

SUP.l9

SAND FILTERSSWITCH

Figure 1 - Pilot's controls and indicators

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FLIGHT MANUAL

2 LIMITATIONSThe limitations specified in the Basic Flight Manual and in the Supplements usedremain applicable and are completed or modified by the following limitations.

2.1 PROHIBITED FLIGHT CONDITIONSthe following are prohibited :

- switching sand filters on again during takeoff or landing phases following anautomatic shutoff,

- simultaneous operation of the cabin heating system and active sand filters inflight.

2.2 WEIGHT LIMITDepending on outside conditions (altitude and temperature), the maximum takeoff orlanding weight must be limited to the maximum twin-engine IGE hover weight.

- With sand filters inactive : Refer to Figure 7 and 8.- With sand filters active : Refer to Figure 9 and 10.

2.3 LTMTTAT|ONS OF ENGTNES (SAND FTLTERS ACTTVE)- The FADEG units AUTOMATICALLY reduce Maximum Takeoff Power N1,

Maximum Continuous Power Nland continuous OEI Nl by 0.31% to comply withT4limits.

3 EMERGENCY PROCEDURESThe emergency procedures specified in the Basic Flight Manual and in theSupplements used remain applicable and are completed or modified by the followingemergency procedures.

3.1 ENGINE FAILURE IN CRUISE FLIGHT

NOTE

On engine failure P2 bleed is automatically switched off when exceedingthe max OEI continuous rating.

lf necessary

r SAND F1LT.............. .. RST then ON.

3.2 IN.FLIGHT ENGINE RESTARTING PROCEDUREBefore restarting the engine, set the "SAND FILT" switch to "OFF'.

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EC 155 81

3.3 MISCELLANEOUS FAULTS AND INCIDENTSo With sand filters switched ON.

o With sand filters switched OFF.

FLIGHT MANUAL

SUP.1904-20 Page 3

EASA APPROVED

r

CORRECTIVE ACTIONS

P2 valveclosed

Sand filtersinactive

Avoid flights in sandy atmosphere

P2 valvein intermediate

position

1 . SAND FILT . . . .

Sand filters are inactive

Avoid flights in sandyatmosphere

CONTINUE THE FLIGHT

For power performances andlimitations, sand filters must beconsidered active

Avoid flights in sandyatmosphere

CONTINUETHE FLIGHT

CORRECTIVE ACTIONS

P2 valveopen

NOTESand filters are active

CONTINUE THE FLIGHT

EC 155 81

r-d-l| -2,2 |

ft]| -2,2 |

E| -2,2 I

IE| -2,2 |

f ,o-l| -2,2 I

r-d-lI -z,z Irr-l| -2,2 |

r-d-l| -2,2 |

l-T-l| -2,2 |

TE| -2,2 |

1 0

t-o-l| -2,2 l

tq| -2,2 |

E| -2,2 I

f-d-l| -2,2 |

E| -2,6 |

EI -4,1 I

8

E| -2,2 |

El -2,2 |

TE| -2,2 |

IEl -2,2 |

folI -3,3 |r-iF-l| -+,4 |

tg| -6,3 |

6

TE| -2,2 |

E]| -2,2 |

rd-l| -z,z ITI| -3,6 |72A1l - s lf€-TlI -e,+ |f-j"2 |t - 8 I

4

tE| -2,2 |

tEI -2,2 |

[T_l| -2,2 |

f-1-gl| -3,6 |

@l - 5 I

@I -6 ,4 |t - ln| -7 ,8 |

Et - 8 I

2

tq| -2,2 |

lr-l| -2,2 |

E| -3 ,4 |

f-E,r-l| -+,4 |

@| -6,3 |

EI -7,6 Iaml - 8 1

tElt - 8 1

-0

r-d-l| -z,z It--lFl| -3,2 |

wI -+,s If-4rl| -s,9 |

FsFl| -7,3 |

@l - 8 Irrll - 8 1

TEt - 8 1

ogsfo\igtot(,

()u{

FLIGHT MANUAL

3.4 FAILURE OF BOTH VEMD SCREENS

VEMD... . . . . . . , . . . . . . . . . .OFF 1 and OFF 2

The emergency page appears on the CAD. Control the AN1 in compliance with thefollowing table :

SAND FILTERS OFFO A T

5 0

4 A

3 0

2 0

1 0

0

- 1 0

-20

H p ( f t

1 2 1 4

x 1 0 0 0 )

tq| -2,2 |

E| -2,2 |

E| -2,2 |

r-d-lI -z,z I

EASA APPROVED

til

SUP.l9Page 4

EC 155 81

04-20

FLIGHT MANUAL

4 NORMAL PROCEDURESThe normal procedures specified in the Basic Flight Manual and in the Supplementsused remain applicable and are completed or modified by the following normalprocedures.

4.1 EXTERIOR CHECKLISTSTATION 1

A D D :

1. Sand fi l ters and ejectors ......... Condition2. Cowlings (Sand filters) Closed

4.2 SPECTAL CHECKS (FTRST FLtcHT OF THE DAy)A D D :

1. SAND FILT . . . . . . . . . . . . . . RST then ON @

2. SAND F|LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF | 3/u ' lD F L. r l

3 , SAND F|1T. . . . . . . . . . . . . . As requi red

4.3 CHECK OF ENGINE POWER MARGIN AND THERMAL MARGINProcedure : Reler to basic FLM section 4.9.

o Automatic power and thermal check (on ground, in cruise, reference check)remains applicable.

. Manual power check (on ground, in cruise, reference check) use figure 2, 5 and 6 onthe present supplement.

o Manual thermal check (on ground, in cruise, reference check) use figure 3 and 4 onthe present supplement.

EASA APPROVED

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04-20 Page 5

EC 155 81

FLIGHT MANUAL

\ tlU Nl l

l 4

t

t; 0t z

t

LrFrp

t-

ttfr m _r m

ffrsl f>al

ffi"),ffi\:\ffiI

&)i.t-

Iri

[${T:o

\ T\

io. J l

9r.sJ il"l.l l'lt-I tT{ 'flJl

fil l\1 l'\.J i'

5 0

40

6 3 0o

[ 2 0o

O A T = 1 5 '

1 0

N l = 98%

N R = 3 4 6 r p m

H p = S o o o f t

T = G T + A T,10

47 ,2 - 3 , 3 = 43 ,9-20

To be co m pa red w i threco rded T-30

-40

60

*v 5 5

uJfgE,oF 5 0aaA G TtE

o45

Ell.

3 4 0tt

6orqos 3 sc)cUJ

-4 AT -3 -2

TORQUE CORRECTTON ( 06 )

C O N D I T I O N S. N O P 2 A I R B L E E D. O N E E N G I N E A T I D L / T R A I N I N G R A T I N G- NR 7 342 rpm- B L E E D V A L V E C L O S E D. S A N D F I L T E R S I N A C T I V E

O N G R O U N D E N G I N EPOWER MARGIN

C H E C K

!$'z+

ffi),,-!-_€ l_

[3--ftffi

Flgure 2

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04-20 Page 6

FLIGHT MANUAL

To be com pa red w i t h ac tua l TOT

,-oZ I, { I

I

EXAMPLE : TOTq = TOTb + ATOT 850 + 2,5 = 852,5

50

o 4 0o

I soo

2 0

1 0

-10

-20

-30

-4040

6o - -

F 3 0oF-

2 A

1 0

ATOT

q

oalr

qo(ooq

lrJ

- 10650 700 750 800 900 950

TOT ( " c )

C O N D I T I O N S- N O P 2 A I R B L E E D- N R ) 3 4 2 r p m- BLEED VALVE CLOSED- SAND F ILTERS INACTIVE

lN FLIGHT IAS - 100 ktA N D O N G R O U N D E N G I N E

T O T M A R G I N C H E C K

mJrt) 2oooo

i oooo

10000

Figure 3

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rSUP.l9EC 155 81

o4-20 Page 7

FLIGHT MANUAL

EXAMPLE : TOTc = TOTb + ATOT 850 - 7,5 = 842,5To be compared w i t h ac tua l TOT

5 0

o 4 Ao

I soo

2 0

1 0

-30

-403 0

6o

; z ool-

1 0

0

ATOT

qorltf

qo

@ool

UJ

-10

-206 5 0 700 750 8 0 0 850

I

TOTb

9oo to t ( ' c ) 9so

C O N D I T I O N S- N O P 2 A I R B L E E D- N R ) 3 4 2 r p m- BLEED VALVE CLOSED- SAN D F ILTERS INACTIVE

IN FLIGHTIAS - 140 kt

E N G I N E T O T M A R G I N C H E C K

ff[tt1 ]-2_oo9o_:-{t sooo -=t+eo'ooF=is6oTff;14000=ts1200q:=t

1 0000

Flgure 4

EC 155 81EASA APPROVED

til

SUP.19o4-20 Page 8

FLIGHT MANUAL

5 0

4 0

6 3 0o

F 2 0

o

O A T = 0 o

Nl = 94o/o

N R = 3 4 6 r p m1 0

H p = 3 0 0 0 f t

G T + A T-10

42 6,3 = 35 ,7-20

To be compared w i t hreco rded T-30

-40

6 0

;v 5 5

UJ=gE,oF 5 0(t)aoE,C'

45

GT

qo\f

o

q€otoo)(\l

UJ

4 0

3 5 -10 -9 -8 -7 aT-6 -s -4

TORQUECORRECTTON(%)

C O N D I T I O N S- STABIL IZED LEVEL FLIGHT- IAS = 140 k t- N O P 2 A I R B L E E D- 900,6 < N1 < 1020./0- 3 4 2 r p m ( N R < 3 5 0 r p m- S A N D F I L T E R S I N A C T I V E

IN FL IGHT ENGINEPOWER MARGIN

C H E C K

-l t\l n{ l\J tN t?I

$,f-+,\l

\

}U:lrfiJrT.l"l'J.

I

z t l. Tr,

Figure 5


ESUP.I9

04-20 Page 9

FLIGHT MANUAL

){t N t}.U Nl fN Ilb:

ffi#t-$

s

:u^-${.bf r9o t

| | l'J.l l'=il-flll fi-l l't.l l'tJ l\

5 0

40

6 3 0c

! 2 0o

O A T = 1 5 '

1 0

N1 = 98o/o

N R = 3 4 6 r p m

H p = 3 o o o f t

T = G T + A T

T = 4 7 , 2 ' 5 , 4 = 4 1 , 8

-10

-20

To be co m pared w i threco rded T-30

-40

60

;v 5 5

tu:foE,ol- 50U)CI'

o c rE

o45

El,t-

3 4 0ttNeo14o)3 3soa?

UJ

-8 -7 -6 AT-5 -4 -3

TORQUE CORRECTTON ( 06 )

C O N D I T I O N S- S T A B I L I Z E D L E V E L F L I G H T- I A S = 1 0 0 k t. N O P 2 A I R B L E E D- 90o/" < N1 1 102o/o- 3 4 2 r p m ( N R < 3 5 0 r p m- S A N D F I L T E R S I N A C T I V E

IN FL IGHT ENGINEPOWER MARGIN

C H E C K

z+l < L

o l

[1*

Flgure 6 '


til

SUP.I9o4-20 Page 10

FLIGHT MANUAL

5 PERFORMANCEThe regulatory performances data specified in the Basic Flight Manual and in theSupplements used remain applicable and are completed or modified by the followingregulatory performance data.

5.1 TWIN.ENGINE HOVER PERFORMANCE PAGES- IGE maximum weight

r Sand filters inactive(figures 7 and 8) ..12 and '13

. Sans filters active(figures g and 10) ,.. 14 and 1 5- OGE maximum weight

r Sand fi l ters inactive(figure 1 1) ....,.....,........ ......,.............. 16. Sans fi l ters active(figure 12) .....................17

5.2 CLIMB PERFORMANCE.. . . . , . . . . . . . . . . . . . . . . . . . . . .18- Determinat ionofweight factor( f iguresl3Aandl38) . . . . . . . . . . . . . . . . . . . . . . . . .20and21- Twin-Engine rate of climb - Vy

. Sand fi l ters inactive(figures 14A and 148)............... .22and23r Sand fi l ters active(figures 15A and 15B) ..................24 and 25

- One-Engine inoperative rate of climb OEI continuous rating - Vy

r Sand fi l ters inactive(figures 16A and 168)............... .26 and27r Sand fi l ters active(figures 17A and 178) ..................28 and 29

- One-Engine inoperative rate of climb OEI 2 min rating - Vy

r Sand fi l ters inactive(figures 18A and 188)..........,.... .30 and 31

5.3 OEI TAKEOFF WEIGHTTO CLIMB AT 150 FT/MIN- Sand fi l ters inactive(figure 19) ......................32- Sand fi l ters active(figure 20) .........................33

5.4 CATEGORY A PERFORMANCE- Maximum Takeoff weight on clear area(figures 21 to 23)...................34 to 36- Maximum Takeoff weight on clear area with increased

sfope(figure 24)................ .......37- Maximum landing weight on clear area(figure 25) .................................... 38- Maximum Takeoff weight from ground helipad(figure 26)......................... 39- Maximum landing weight on ground helipad(figure 27)..................,,.........40

EASA APPROVED

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EC 155 81

o4-20

FLIGHT MANUAL

5.1 TWIN ENGINE HOVER PERFORMANCE

coNpr i l o [ sH E I G H T : 6 f t

- B O T H E N G I N E S A T T A K E O F F R A T I N G- N R N O R M- S A N D F I L T E R S I N A C T I V E

TWIN-ENGINE HOVERP E R F O R M A N C E I G EMAXIMUM WEIGHTS

ooo

x

- 1 5o-I

;o

5 PxE

o.

qt!olto=(LqUJo n

6 vo;@9<)a?

UJ

3 0 0 0 3 5 0 0 4 0 0 0 4500 ( k g ) 5000

7000 8 0 0 0 9 0 0 0 1 0 0 0 0 ( l b ) 1 1 0 0 0W E I G H T

E X A M P L E : Hp = l oooo f t

O A T = 1 0 " CW E I G H T = 4 1 0 0 k g

N

f"g)l<

\-\

lN-

\(

\\

k'\-- -

_\st.\-

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IN \

l t r '

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- 9

lo@sf

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Figure 7


E

SUP.1904-20 Page 12

FLIGHT MANUAL

C O N D I T I O N S- H E I G H T : 6 f t- B O T H E N G I N E S A T T A K E O F F R A T I N G. N R N O R M- S A N D F I L T E R S I N A C T I V E

TWIN.ENGINE HOVERP E R F O R M A N C E I G EMAXIMUM WEIGHTS

ooo

x

; 1 5

ctI

oR O" o

x

E

o.

4

qll.

olto=o.

ulo

qCD€toelrJ 3 0 0 0 3 500 4000 4500 kg 5 000

r l l

70 00l r r r r l l

8000r r r l l

9 0 0 0r r l r r r r l r r r r l

i o o o o ( l b ) 1 1 o o o

W E I G H T

E X A M P L E : Hp = 6ooo f t

O A T = 2 0 o C

W E I G H T = 4 4 0 0 k g

o).Y

€ I.O^

lOo=F--\

l.. t y '

t?_t l

FToI I m a x i m u m H o

1 3 0 0 0 f t

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Figure 8


rSUP.19

Page 1304-20

FLIGHT MANUAL

C O N D I T I O N S- H E I G H T : 6 f t- B O T H E N G I N E S A T T A K E O F F R A T I N G- N R N O R M- S A N D F I L T E R S A C T I V E

T W I N - E N G I N E H O V E RP E R F O R M A N C E I G EM A X I M U M W E I G H T S

ooo

x

: ' uo.

5go

x

5o.r

4

oqzoU'

l!o

o-q)UJo

qg)@Ioc?

lrJ

+ 6 0 '

3 0 0 0 3500 4 0 0 0 4 5 0 0 ( k s ) s000

7000 8 0 0 0 9 0 0 0 1 0 0 0 0 ( l b )

W E I G H T

1 1 0 0 0

E X A M P L E : H P = 9 0 0 0 f t

O A T = 1 0 " CW E f G H T = 4 2 4 0 k g

WND WNDuREsnchrt

lDrREcnor!

Figure 9

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EC 155 81

o4-20 Page

FLIGHT MANUAL

C O N D I T I O N S- H E I G H T : 6 t t- B O T H E N G I N E S A T T A K E O F F R A T I N G- N R N O R M- S A N D F I L T E R S A C T I V E

TWIN-ENGINE HOVERPERFORMANCE IGEMAXIMUM WEIGHTS

ooo

x

.E 15

CLI

_ o5 0

o

x

E

o,I

4

eqzoa

l!o=o.

UJoqCD@tloa?

UJ 3000 3500 4000 4500 ( k g ) s000

7000 8000 9000 1 0 0 0 0 ( t b )

W E I G H T

1 1 0 0 0

E X A M P L E : Hp = Sooo f t

O A T = - 1 0 o CW EIG HT = 4628 kg

o)J'

ou)@sf

t l

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a\ f ' . m a x i m u m H o1 3 0 0 0 f t

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Figure 10

EASA APPROVED

ESUP.lI

1 5

EC 155 81

04-20 Page

FLIGHT MANUAL

C O N D I T I O N S- B O T H E N G I N E S A T T A K E O F F R A T I N G- ZENO WIND- N R N O R M. SAN D F ILTERS INACTIVE

TWIN-ENGINE HOVERPERFORMANCE OGEMAXIMUM WEIGHTS

ooo

x

o-r

ooo

x

E5 v

o.

qtLoll.

o=o.aIJJ:E

qct)cotoc?

tU

3 0 0 0 3500 4000 4500 ( k g ) 50 00

7000 8000 9000 1 0 0 0 0 ( l b ) 1 1 0 0 0W E I G H T

E X A M P L E : Hp = Tooo f t

O A T = 2 O ' CW E IG HT = 4000 kg

o).Y

\ fr' o!O@

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r\ IT ax i t1 3 (

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t

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Figure 11


til

SUP.l9Page 1 6o4-20

FLIGHT MANUAL

C O N D I T I O N S- B O T H E N G I N E S A T T A K E O F F R A T I N G. Z E R O W I N D- N H N O R M. S A N D F I L T E R S A C T I V E

TWIN-ENGINE HOVERP E R F O R M A N C E O G EMAXIMUM WEIGHTS

oc)o

x

o-

ooor

x

E5 v

oI

ogzoCI'

tLo=o.C"ulI

q(D@toa?

uJ

3000 3500 4000 4500 ( k g ) s000

7000 8000 9000 1 0 0 0 0 ( l b ) 1 1 0 0 0W E I G H T

E X A M P L E : Hp = 45oo f t

O A T = 1 0 o C W E I G H T = 4 6 6 3 k g

I(').-

nn axl1 3

Il . /

l lm u m H000 f t

I IorO@

-_sl

t l

F

/ro

. o 4

lJ,l

=

\,\"r. { c)

v)

ao

\ J \ Sttro

T \ t t Yozf

=

) i )-l \ ioo x

\ l

\Id\

\ec\ Sr& r l

\ \\ f, \ ,\) S \\ )

V,fJ\..1\ \

\ x \ \ \ \\

)7\.1r.

\ \.\

\ \ \-)\ p tt\ \

t

-I\ \ xt \

I

t

\ l il \\

\ R] t.l \ I

\

1\

\II \ t t

\ +J \ \ \

\ .+I

\y

t a \ \\\ l

\ \ \

\nI \ \ \ \

\ \I

l l

\ \

Flgure 12

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EC 155 81

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FLIGHT MANUAL

5.2 CLIMB PERFORMANCEThe determination of the F|/C requires the use of reduced weights (Wq).In order to simplify the figures and not to confuse "reduced weight" for "actualweight", the W<r parameter is converted into a dimensionless parameter known as"WEIGHT FACTOR" (Wo in kg divided by 1000).

DETERMINATION OF RATE OF CLIMB

4 curves are necessary to determine the R/C. The first two curves are used todetermine the weight faclor (Figures 13A and 1 3B).

FIGURES 13A and 138

14A and 14815A and 158

+ F IGURES 16Aand16Bl7Aand 17818A and 188

@ w E r c H r I N D E X @ R/c

,1

ogUJJ

o-=llJxu{\io(oc\l

llJ

t

EASA APPROVED

til

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-/, l - - -

. TIII

EC 155 81

FLIGHT MANUAL

PAGE INTENTIONALLY LEFT BLANK

EASAAPPRoVED Ec 1s5 Bl SUp.l g

E 04-20 pagel9

FLIGHT MANUAL

C O N D I T I O N S- N O C O N D I T I O N

I N D E X O F W E I G H TF O R D E T E R M I N I N G

R A T E O F C L I M B

oq

=IU'q@

o

d)c!

lrJ

30 40o A T ( ' C )

E X A M P L E : O A T = 0 o C

H p = 4 0 0 0 f tT R A N S F E R S C A L E

Flgure 13A

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FLIGHT MANUAL

C O N D I T I O N S

- N O C O N D I T I O N

-

I N D E X O F W E I G H TF O R D E T E R M I N I N G

R A T E O F C L I M B

oggo

=q@o

o)q

ut6 . 5 7 7 . 5

I N D E X O F W E I G H T

E X A M P L E : T R A N S F E R S C A L E

A C T U A L W E I G H T =

= $

4 2 0 0 k gI N D E X O F W E I G H T = 4 . 6 2 5

Figure 138

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EC 155 Bl

04-20 Page

FLIGHT MANUAL

C O N D I T I O N S- B O T H E N G I N E S A T M A X C O N T I N U O U S R A T I N G- N O P 2 A I R B L E E D. L / G U P- N R N O R M

. S A N D F I L T E R S I N A C T I V E

TWIN.ENGINERATE OF CLIMB Vy

qt!otJ-o=o-I6

=ot€soa?

ul

E X A M P L E : O A T = 0 ' C

Hp = Sooo f tT R A N S F E R S C A L E = 7 . 8

Figure 14A

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FLIGHT MANUAL

C O N D I T I O N S- B O T H E N G I N E S A T M A X C O N T I N U O U S R A T I N G- L / G U P- N H N O R M

- S A N D F I L T E B S I N A C T I V E

TWIN-ENGINERATE OF CL IMB Vy

qor4t(r)oUJz3qcoo(D(\l

llJ

2 000R/C ( ft /m in )

E X A M P L E : T R A N S F E R S C A L E = 7 . 8

I N D E X O F W E I G H T = 5 . 5R/C = 1234 ft/m in

Flgure 148


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FLIGHT MANUAL

C O N D I T I O N S- B O T H E N G I N E S A T M A X C O N T I N U O U S R A T I N G- L /G UP- N R N O R M- S A N D F I L T E R S A C T I V E

TWIN-ENGINERATE OF CLIMB Vy

oqzoo

l.t.o=Eoo

=oCOtoq?

UJ

30 40o A T ( " C )

E X A M P L E : O A T = 0 ' C

Hp = 17ooo f tT R A N S F E R S C A L E = 6 . 7

Figure 15A

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FLIGHT MANUAL

C O N D I T I O N S- B O T H E N G I N E S A T M A X C O N T I N U O U S R A T I N G. L /G UP- N R N O R M

: S A N D F I L T E R S A C T I V E

TWIN-ENGINERATE OF CLIMB Vy

qoroctolrJz=qoo

o)s{

IIJ

2 000R/C ( ft /m in )

EXAM P LE : T R A N S F E R S C A L E = 6 . 7

I N D E X O F W E I G H T = 5 . 5R/C = 1091 f t lm in

Figure 158


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FLIGHT MANUAL

C O N D I T I O N S. O N E E N G I N E A T C O N T I N U O U S P O W E R R A T I N G- N O P 2 A I R B L E E D- L /G UP- N R = 3 3 0 r p m- S A N D F I L T E R S I N A C T I V E

RATE OF CLIMBONE ENGINE INOPERATIVE

Vy

qll-

otLf,

Lg

o

=g)co*oq?

tu30 40

o A T ( ' C )

E X A M P L E : O A T = 0 o C

Hp = o f tT R A N S F E R S C A L E = 1 7 . 2

Figure 16A

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EC 155 81

FLIGHT MANUAL

C O N D I T I O N S. O N E E N G I N E A T C O N T I N U O U S P O W E F R A T I N G- L/G UP- N R = 3 3 0 r p m

: SAND F ILTERS INACTIVE

RATE OF CL IMBONE ENGINE INOPERATIVE

Vy

olgoC?(ooUJz3q@og)

o{

lrJ gbt

E X A M P L E : T R A N S F E R S C A L E = 1 7 . 2

I N D E X O F W E I G H T = 4 . 5R/C = 282 ft/m in

( ft /m in

Flgure 168


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FLIGHT MANUAL

C O N D I T I O N S- O N E E N G I N E A T C O N T I N U O U S P O W E R R A T I N G- L/G UP- N R = 3 3 0 r p m

: SAND F ILTERS AcT IVE

ONE ENGINE INOPERATIVERATE OF CLIMB Vy

oqzoq,

lrl

G

Lo*(t)€otoo?

IrJ

-40 30 40o A T ( ' C )

dB

EXAM P LE : OAT = -5 'C

Hp = 14000 f tT R A N S F E R S C A L E = 1 7 . 4

ffi"fi:oo;

C

\

iftr}

Flgure 17A

EC 1s5 81EASA APPROVED

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SUP.l9o4-20 Page 28

FLIGHT MANUAL

C O N D I T I O N S- O N E E N G I N E A T C O N T I N U O U S P O W E R R A T I N G- L/G UP- NR = 330 rpm- SAND F ILTERS ACT IVE


Vy

3 0

c)q

o(Dc!)oIJJ

z=q6o

o)ol

ul -9ffi 500 1000 1500R/C ( ft/m in )

E X A M P L E : T R A N S F E R S C A L E = 1 7 . 4

I N D E X O F W E I G H T = 4 . 5R/C = 290 f t lm in

I V

L LA I- J_I I t_l_ L I / / /I d,l I I I I I / L J A

I

ll t /'€/ /

,l /so,/ / /t_ /i!L / 3t /I V V /e / / /v J J -+"T Y / /

I ,/ A rL,?-Y

,I- 1 -

I I I /4r/"/ I / / /Al I I / /

II

4) /cD)

/

I I,/

/ / / a/ / / /

I /I / /

//

/ tl/

/

/

Figure 178

EASA APPROVED

til

SUP.1I29

EC 155 81

04-20 Page

FLIGHT MANUAL

C O N D I T I O N S- O N E E N G I N E A T 2 m i n P O W E R R A T I N G- N O P 2 A I R B L E E D. L /G UP- N R = 3 3 0 r p m- S A N D F I L T E R S I N A C T I V E


Vy

q1!ol!f=o-Lo

=g)

ortoc?

UJ

EXAM PLE : O A T = 0 o C

H p = 9 o o o f tT R A N S F E R S C A L E = 2 1 . 0

Figure 18A

EASA APPROVED

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FLIGHT MANUAL

C O N D I T I O N S- O N E E N G I N E A T 2 m i n P O W E R R A T I N G. L / G U P- N R = 3 3 0 r p m- S A N D F I L T E R S I N A C T I V E

RATE OF CL IMBO N E E N G I N E I N O P E R A T I V E

Vy

3 0

c,

: 5e)(v)

ollJz

=q@o

o)ol

A 0-c 0 0 5 0 0 1 0 0 0 1 5 0 0

n/C ( ft /m in )

E X A M P L E : T R A N S F E R S C A L E = 2 1 , 0

I N D E X O F W E I G H T = 4 . 5R/C = 400 f t /m in

I V /'J

I V / t// /

t ) I I I /,l

/ / /l r " I I I / / / A / 7

-7J

I r f, -f1 L / /

I I ,l I / ) sq,1

/ / / /I I I I 1-'',1-1_/ / I / &/ / /L I I I I / / /a I I / /

I [+o/ / /T- 7 7-

I / Lq,'/ L / / / /I

t / / I/ I y',,,i/ l / 1 /

/ / / / /IO

I /cD)

/J

I / / ,/

r l f // l / I / I / /,J

//

/ /t l / I

A /L] / / / /

t l l / t A ^r_l nI

/ / ) A / // / / / /

Flgure 188

EASA APPROVED

til

SUP.l931

EC 155 Bl

04-20 Page

FLIGHT MANUAL

5,3 OEI TAKEOFF WEIGHT TO CLIMB AT 150 FT/MIN

C O N D I T I O N S- O N E E N G I N E A T C O N T I N U O U S P O W E R R A T I N G- N O P 2 A I R B L E E D- L /G UP- T A S = V y- S A N D F I L T E R S I N A C T I V E

II r lxeoFF wErcHTs PERMTTnNGI CLIMB AT 150 ft lmin 1000 ftI ABOVE GROUND WrrH

I oNE ENGTNE TNOPERATTVEI

ooo

x

o-I

ooo

x

E

s -o-

qttoa

tl.6

qCD@

soc?

lrJ

3000 3500 4000 4500 5000

7000 8000 9000 1 0 0 0 0 ( r b ) 1 1 0 0 0WEIG HT


O A T = 1 0 ' CW E I G H T = 4 1 0 0 k g

CD

olr)

st

l t

m a x i m u n1 3 0 0 0 '

HCI't

F

tft

llJ

=\. ri a

o

\ x lr'IEo

J t t s \ _9 ==

.</ \

\\ N\

=x

:'.j.>\ \ !$\ \ =

I i..' i\.' c

t o\

\ \ \' {o

\ )\ ) ! \ \ S\

- iu(

il\ \\ x

\\\ \

:\a -il\ \ XI \

\ \$

q.l \\

\

\)

.tl{d

I(\

\6 _

a\

\\\

|a \I

It

t

\ J\\

Flgure 19


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FLIGHT MANUAL

C O N D I T I O N S- O N E E N G I N E A T C O N T I N U O U S P O W E R R A T I N G- L /G UP- T A S = V y- SAND F ILTERS ACT IVE- N R = 3 3 0 r p m

II TAKEOFF WEIGHTS PERMITTING

I cuMB AT 150 frlmtn rooo ftI ABOVE GROUND WtrHI

oNE ENGTNE TNOPERATTVE

I

ooc)

x

I

ooo

x

E

5 -o-I

0qzoU)

tr.oF

ot4oG'(o

@ol

llj

3000 3500 40 00 4500 ( k g ) 5000

700 0 8000 9000 1 0 0 0 0 ( t b ) 1 1 0 0 0W E I G H T


O A T = 2 0 " CW E I G H T = 4 1 4 0 k g

o,-t

orO@

t i t lMAX . Dens i t y

A l t i tude\ lgooo f t

f--$I

l u

l o

/ .LU

3U)v)

\) \E,CI\,

\ \ o f

f a\

\7

Ct=X

/F'.-g

f$o '

=

\ aq\ S >*g

\\

\ I \\

\ \.

\ _rta? x\\

\\ \ I

\ lla' Kl \ S

\\ q \

) t \\

) t.. \ \

l )I

x l, 3 1 o \ I \ \t ' J

\ta\ I

\ \

\ I

\ & * \ J\ \ l

Flgure 20

EASA APPROVED

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SUP.I9EC 155 81

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FLIGHT MANUAL

5.4 CATEGORY A PERFORMANCE

C O N D I T I O N S- S W I T C H " R P M ' T O " N O R M "- N O P 2 A I R B L E E D- VTOSS = 40 k t (TAS)- V1 = 35 kt (TAS)- S A N D F I L T E R S I N A C T I V E

MAXIMUM TAKEOFFWEIGHT

ON CLEAR AREAVTOSS = 40 kt

2 0 0 0 0

1 5 0 0 0

ooo

x

o-I

;o

4 Px

E

o-I

1 0 0 0 0

so00

otq

oa

lJ.

os

O 3000 3500 4000 4 s 0 0 ( k g ) 5 0 0 0(D@

3 7000 8000 9000 10000 ( l b ) 11000a?

W E I G H T

Iotl<

olo@sf

IgUJ

sa

'?'tVJ

oE-o

=-(?t

H T = 7250 f t f

=,. ti

..t.,./o\ Yx!5

i f l -f\. >a

\.\ \ S -l\ l 'go

\ \ a--trQ

! - 1

..--$'-:a.g

-l?o \

Yo \ \.o

x

o\ \ \ \

\ \\ \ \

a 2 S \ \ \

N ) N\ '$t I

Figure 21

EASA APPROVED

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FLIGHT MANUAL

C O N D I T I O N S- S W I T C H ' R P M " T O ' N O R M "- N O P 2 A I R B L E E D- V T O S S = 5 0 k t ( T A S )- V1 = 45 k t (TAS)- S A N D F I L T E H S I N A C T I V E



2 0 0 0 0

1 5 0 0 0

ooo

x

o-

oo

4 9x

5o--

1 0000

5000

(\l

qlJ.oo

lJ-

o

ro

F

qCD@!foa?

uJ

3 0 0 0 3500 4 0 0 0 4 s 0 0 ( k g ) 5 0 0 0

7 0 0 0 8000 9000 10000 ( l b ) 11000

W E I G H T

o)- - - L

olO@r1.

il

FI

guJ=ct)ct)o0co=

x

Ho = 7250 t t

Figure 22


til

SUP.l9o4-20 Page 35

FLIGHT MANUALC O N D I T I O N S- S W I T C H " R P M ' T O ' N O R M ' '- N O P 2 A I R B L E E D- VTOSS = 60 k t (TAS)- V1 = 5s k t (TAS)- S A N D F I L T E R S I N A C T I V E



2 0 0 0 0

1 s 0 0 0

ooo

x

o-

;o

4 Px

5o-

1 0 0 0 0

5 0 0 0

c)qlroo

ILo(o

qg,@soal

uJ

3 0 0 0 35 00 4000 45 00 ( kg ) 5000

7000 8000 9000 10000 ( t b ) 11000

W E I G H T

o)--ort)co$

il

)4

Fr

. .o /gllJ

\..\ I

\ l \5a

a\

v)

oE

H o = l z , 5 0 Ft o

:)=

...a.l7 ..'.Jq..

xSwo \ \. {

\ l \{. l ol \\

\. l\ l

\l I itq

fo. \ \ \ s19

\ ^ l:<o l

RI

o

{..q

) \ \a\ \ \

\ .1 x- \ \t( \ \

\s;O

\ \ \

\\

\i o\

\\

\ =)\ \

\'.l

\

N ,o \ \\

Ii

II

\r ' \ .

Figure 23


trlSUP.l9

o4-20 Page 36

FLIGHT MANUAL

C O N D I T I O N S- S W I T C H " R P M " T O " N O R M "- N O P 2 A I R B L E E D- V T O S S = 6 0 k t ( T A S )- V1 = 55 kt (TAS)- S A N D F I L T E R S I N A C T I V E


ON CLEAR AREAWITH INCREASED SLOPE

20000

1 5000

ooo

x

o-I

;o

4 Px

5o.I

1 0000

5 0 0 0

NqUJG

oJ

aztJ.

oo

ll-

o(0

qcl)@toa?

IJJ

3 0 0 0 35 00 4000 4 5 0 0 ( k g ) s 0 0 0r l l

7000r l l

8 0 0 0 9000 10000 ( l b ) 11000

W E I G H T

io)

J

or.cl@!t

t l

)at-

("oolrJ

\.=a

\a \

r.t )

oE

H O = 7 5 0 ft(5

=f,=

'.aq? 'r\i q>

xS

-'rto \\

::'o-r . f

\ itq

fo.:l

p^o

it.,L

)i^(

tt\

\o

t( e,o

\ u\

\

\ \s

\b \I

It

t \

Flgure 24


ESUP.I9

o4-20 Page 37

FLIGHT MANUAL

C O N D I T I O N S- S W I T C H ' R P M ' T O ' N O R M "- N O P 2 A I R B L E E D- S A N D F I L T E R S I N A C T I V E

MAXIMUM LANDINGWEIGHT

ON CLEAR AREA

2 0 0 0 0

1 5 0 0 0

ooo

x

o.

oo

4 Px

5o--

1 0 0 0 0

5 0 0 0

q

gtI.oa

l!oa0

qcD@Ioa?

lrJ

3000 3500 4000 4 5 0 0 ( k g ) 5 0 0 0

7000 8000 9000 1 0000 ( rb )11 000

W E I G H T

o,J

oroosf

) . aFI

\i . .o

gUJ

\.=CD

\\(t,

oE,

ita\ H o = 7 2

- / l5 0 ft o

=f,=

"i$*rI

? t ]

w 59)-..'\.,

\\

x

=c \. {

\ l\ :\ l

tI:g-l

\ \-\ - \

\ \- --l -lirQ\ , ;

do\ \ r \

\ \ \ S{J

Ip ^ to

i...qi-:{ \ \ \ \ aR]t.\

I ,// t . ,

\ \ a \ {\ l

t . l {. \ \\ \I

t( \ \ aa

\ \ \ \ \\ \

\\{ c \ \

\ \\ \

\

\ \\ \ \

ri

\\

\

\ I \ \ \ t'i\ \

N o\

\\\ \ *

tI

II

\\'.!

Figure 25


rSUP.l9

04-20 Page 38

FLIGHT MANUAL

C O N D I T I O N S- S W I T C H " R P M " T O ' ' H I G H "- N O P 2 A I R B L E E D. S A N D F I L T E R S I N A C T I V E MAXIMUM TAKEOFF WEIGHT

FROM GROUND HEL IPAD

ooo

x

o-

1 0

oo

4 o

x

E

o.

qtl.

oa

l!

oo-OUJoq(D@tfoa?

UT3000 3s00 4000 4500 ( xg ) 5000

7000 8000 9000 10000 ( t b ) 1 1 0 0 0

EXAM PLE: Hp = looo f t

OAT = 20" CW E I G H T = 3 9 5 0 k g

Io,

l(

oroCE'sf

il

Ifn

il=aaL'(E(9

\* 3n,=:)

{'g, Xcf

H o = 7 2 5 0 ft I

r.'../a!t -l

\ 7 \

r\

..R\ s \ \

qt X .t. l

-x )

\d.<.

o o r'Ti:^l

\\

\ \ \ ' - . I\ l' ..€i{\ \

\ \ \\-\{) \ \ \ \ I8\

\ \ })\

\\ \ \ l l

\\

\ ;i \\ \ \ l l

\ \s \ \ [li\

\ \ I \'\ JT

R \l\\{ \ \

\- \s

Figure 26


E

SUP.I9o4-20 Page 39

FLIGHT MANUAL

C O N D I T I O N S- S W I T C H ' R P M " T O ' H I G H "- N O P 2 A I R B L E E D

: s A N D F T L T E R S T N A C T T V E MAXIMUM LANDING WEIGHT

ON GROUND HEL IPAD

2 0

ooo

x

o.I

oo

4 oxE

o-I

(\t

ett

ooII

C)o-

t-{o@toa?

lrJ3000 3500 4000 4500 ( kg ) s000

7000 8000 9000 10000 ( ] b ) 11000

EXAMPLE: Hp = 2000 f t

OAT = 20 ' CW E I G H T = 3 9 0 0 k g

o).Y

orJ)@+

t l

FrI

3(naot

,i, o5

)"g f

Ex=\

.) H f = 7250 f t

) i' '!v,u ) \. .N\\

I?l \\ *

/t

$\r'l

('j-

\ \ \t ' \ \ \ \ .r"l

\\ \ \ \ \ \

I3o

t \ \! . \

\Yi

$i\

\\ \ \ \ \

\ \-\

\ .9. S\\ \ \ c \

\ x,.%l

r\

\

) \

Figure 27


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SUP.I9o4-20 Page 40

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EASA APPROVED