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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
EASA APPROVED
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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 )
SUP. 19S U P . 1 9SUP. 19S U P . 1 9SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19S U P . 1 9S U P . 1 9S U P . 1 9S U P . 1 9SUP. 19
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04-2004-2004-2004-20o4-2004-2004-2004-2004-2004-2004-2004-2004-2004-20o4-2004-2004-20o4-2004-2004-2004-2004-20
S U P . 1 9S U P . 1 9S U P . 1 9SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19SUP. 19S U P . 1 9SUP. 19SUP. 19SUP. 19S U P . 1 9SUP. 19SUP. 19S U P . 1 9SUP. 19SUP. 19
2122232425262728293031323334353637383940
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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SUP.l904-20 Page 2
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 |
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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
EASA APPROVED
ESUP.l9EC 155 81
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
$,f-+,\l
\
}U:lrfiJrT.l"l'J.
I
z t l. Tr,
Figure 5
EC 155 81EASA APPROVED
ESUP.I9
04-20 Page 9
FLIGHT MANUAL
){t N t}.U Nl fN Ilb:
ffi#t-$
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 '
EC 155 81EASA APPROVED
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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SUP.l9Page 1 1
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
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;o
5 PxE
o.
qt!olto=(LqUJo n
6 vo;@9<)a?
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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
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Figure 7
EC 155 81EASA APPROVED
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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
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o.
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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--\
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Figure 8
EC 155 81EASA APPROVED
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
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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
EASA APPROVED
E
SUP.l91 4
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
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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'
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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
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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
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Figure 11
EC 155 81EASA APPROVED
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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 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
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oI
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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
EASA APPROVED
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EC 155 81
04-20
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
SUP.l9Page 18
-/, l - - -
. TIII
EC 155 81
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PAGE INTENTIONALLY LEFT BLANK
EASAAPPRoVED Ec 1s5 Bl SUp.l g
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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
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
EASA APPROVED
rSUP.l9EC 15s 81
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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
EASA APPROVED
til
SUP.lI21
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
EASA APPROVED
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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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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
EASA APPROVED
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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
EC 155 81EASA APPROVED
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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
EASA APPROVED
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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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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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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
RATE OF CLIMBONE ENGINE INOPERATIVE
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
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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- 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
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
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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
E X A M P L E : Hp = 5ooo f t
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
EC 155 81EASA APPROVED
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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
E X A M P L E : Hp = 3ooo f 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$o '
=
\ aq\ S >*g
\\
\ I \\
\ \.
\ _rta? x\\
\\ \ I
\ lla' Kl \ S
\\ q \
) t \\
) t.. \ \
l )I
x l, 3 1 o \ I \ \t ' J
\ta\ I
\ \
\ I
\ & * \ J\ \ l
Flgure 20
EASA APPROVED
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FLIGHT MANUAL
5.4 CATEGORY A PERFORMANCE
C O N D I T I O N S- S W I T C H " R P M ' T O " N O R M "- N O P 2 A I R B L E E D- VTOSS = 40 k t (TAS)- V1 = 35 kt (TAS)- S A N D F I L T E R S I N A C T I V E
MAXIMUM TAKEOFFWEIGHT
ON CLEAR AREAVTOSS = 40 kt
2 0 0 0 0
1 5 0 0 0
ooo
x
o-I
;o
4 Px
E
o-I
1 0 0 0 0
so00
otq
oa
lJ.
os
O 3000 3500 4000 4 s 0 0 ( k g ) 5 0 0 0(D@
3 7000 8000 9000 10000 ( l b ) 11000a?
W E I G H T
Iotl<
olo@sf
IgUJ
sa
'?'tVJ
oE-o
=-(?t
H T = 7250 f t f
=,. ti
..t.,./o\ Yx!5
i f l -f\. >a
\.\ \ S -l\ l 'go
\ \ a--trQ
! - 1
..--$'-:a.g
-l?o \
Yo \ \.o
x
o\ \ \ \
\ \\ \ \
a 2 S \ \ \
N ) N\ '$t I
Figure 21
EASA APPROVED
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SUP.19EC 155 81
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FLIGHT MANUAL
C O N D I T I O N S- S W I T C H ' R P M " T O ' N O R M "- N O P 2 A I R B L E E D- V T O S S = 5 0 k t ( T A S )- V1 = 45 k t (TAS)- S A N D F I L T E H S I N A C T I V E
MAXIMUM TAKEOFFWEIGHT
ON CLEAR AREAVTOSS = 50 kt
2 0 0 0 0
1 5 0 0 0
ooo
x
o-
oo
4 9x
5o--
1 0000
5000
(\l
qlJ.oo
lJ-
o
ro
F
qCD@!foa?
uJ
3 0 0 0 3500 4 0 0 0 4 s 0 0 ( k g ) 5 0 0 0
7 0 0 0 8000 9000 10000 ( l b ) 11000
W E I G H T
o)- - - L
olO@r1.
il
FI
guJ=ct)ct)o0co=
x
Ho = 7250 t t
Figure 22
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FLIGHT MANUALC O N D I T I O N S- S W I T C H " R P M ' T O ' N O R M ' '- N O P 2 A I R B L E E D- VTOSS = 60 k t (TAS)- V1 = 5s k t (TAS)- S A N D F I L T E R S I N A C T I V E
MAXIMUM TAKEOFFWEIGHT
ON CLEAR AREAVTOSS = 60 kt
2 0 0 0 0
1 s 0 0 0
ooo
x
o-
;o
4 Px
5o-
1 0 0 0 0
5 0 0 0
c)qlroo
ILo(o
qg,@soal
uJ
3 0 0 0 35 00 4000 45 00 ( kg ) 5000
7000 8000 9000 10000 ( t b ) 11000
W E I G H T
o)--ort)co$
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
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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
MAXIMUM TAKEOFFWEIGHT
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
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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- 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
EC 155 81EASA APPROVED
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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
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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
EC 155 81EASA APPROVED
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