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FLIGHT MANUAL F eurocopter U an EADs correanv FLIGHT MANUAL EC 15581 SUPPLEMENT SAND FILTERS INSTALLATION IM P O R T A N T NOTE The information contained herein supplements or supersedes the information given in the basic flight manual and/or supplements listed in supplement 0. The effectivity of the supplement at the latest revision is specified on the List of Effective Pages. THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MANUAL WHEN THE EQUIPMENT MENTIONED ABOVE IS INSTALLED ON THE AIRCRAFT. EU ROCO PTER Directlon Technique Support A6roport internatlonal Marseille-Provence 13725 Marignane Cedex - France EASAAPPROVED E SUP.19.Pl EC 15581 o4-20 Page1
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May 22, 2022

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FLIGHT MANUAL
EC 15581 SUPPLEMENT
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 iven i 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 f E 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 E EQUIPMENT 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 t A6roport internatlonal Marseil le-Provence 13725 Marignane Cedex - France
EASA APPROVED
EASA CERTIFICATION (1) Page Revision Code
R: Revised, to be replaced N: New, to be inserted
FLIGHT MANUAL
SUPPLEMENT PAGE DATE ( 1 ) SUPPLEMENT PAGE DATE ( 1 )
SUP. 19 S U P . 1 9 SUP. 19 S U P . 1 9 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 S U P . 1 9 S U P . 1 9 S U P . 1 9 S U P . 1 9 SUP. 19
P1 1 P5 1
1 2 3 4 5 6 7 8 9
1 0 1 1 1 2 1 3 1 4 1 5 1 6 1 7 1 8 1 9 20
04-20 04-20 04-20 04-20 o4-20 04-20 04-20 04-20 04-20 04-20 04-20 04-20 04-20 04-20 o4-20 04-20 04-20 o4-20 04-20 04-20 04-20 04-20
S U P . 1 9 S U P . 1 9 S U P . 1 9 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 SUP. 19 S U P . 1 9 SUP. 19 SUP. 19 SUP. 19 S U P . 1 9 SUP. 19 SUP. 19 S U P . 1 9 SUP. 19 SUP. 19
21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40
o4-20 04-20 04-20 04-20 o4-20 04-20 04-20 04-20 04-20 04-20 04-20 04-20 04-20 a4-20 04-20 o4-20 04-20 04-20 04-20 04-20
LIST OF THE I-ATEST NORMAL APPROVED REVISIONS
NORMAL REVISION : 0 D A T E : 0 8 1 0 7 1 2 0 0 4
Approved by DGAC on 08/0712004 according to the article 10.3 of the CE 1592/2002 regulation
No. Date I No. Date
04-20
FLIGHT MANUAL
GENERAL The sand filters installation is designed to prevent the ingress ol sand into the engines in 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 continuous rating).
1.1 PILOT'S CONTROLS AND INDICATORS
OVERHEAD PANEL CAD
c g o)(o
q ln u)
SUP.l9
EASA APPROVED EC 155 81
E 04-20 Page 1
FLIGHT MANUAL
2 LIMITATIONS The limitations specified in the Basic Flight Manual and in the Supplements used remain applicable and are completed or modified by the following limitations.
2.1 PROHIBITED FLIGHT CONDITIONS the following are prohibited :
- switching sand filters on again during takeoff or landing phases following an automatic shutoff,
- simultaneous operation of the cabin heating system and active sand filters in flight.
2.2 WEIGHT LIMIT Depending on outside conditions (altitude and temperature), the maximum takeoff or landing 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 with T4limits.
3 EMERGENCY PROCEDURES The emergency procedures specified in the Basic Flight Manual and in the Supplements used remain applicable and are completed or modified by the following emergency procedures.
3.1 ENGINE FAILURE IN CRUISE FLIGHT
NOTE
On engine failure P2 bleed is automatically switched off when exceeding the max OEI continuous rating.
lf necessary
r SAND F1LT.............. .. RST then ON.
3.2 IN.FLIGHT ENGINE RESTARTING PROCEDURE Before restarting the engine, set the "SAND FILT" switch to "OFF'.
EASA APPROVED
EC 155 81
3.3 MISCELLANEOUS FAULTS AND INCIDENTS o With sand filters switched ON.
o With sand filters switched OFF.
FLIGHT MANUAL
P2 valve in intermediate
CONTINUE THE FLIGHT
For power performances and limitations, sand filters must be considered active
Avoid flights in sandy atmosphere
CONTINUETHE FLIGHT
CORRECTIVE ACTIONS
CONTINUE THE FLIGHT
EC 155 81
r-d-l | -2,2 |
l-T-l | -2,2 |
TE | -2,2 |
1 0
tg | -6,3 |
TE | -2,2 |
E] | -2,2 |
rd-l | -z,z I TI | -3,6 | 72A1 l - s l f€-Tl I -e,+ | f-j"2 | t - 8 I
4
E t - 8 I
tEl t - 8 1
w I -+,s I f-4rl | -s,9 |
FsFl | -7,3 |
TE t - 8 1
() u{
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 the following table :
SAND FILTERS OFF O A T
5 0
4 A
3 0
2 0
1 0
tq | -2,2 |
E | -2,2 |
E | -2,2 |
FLIGHT MANUAL
4 NORMAL PROCEDURES The normal procedures specified in the Basic Flight Manual and in the Supplements used remain applicable and are completed or modified by the following normal procedures.
4.1 EXTERIOR CHECKLIST STATION 1
A D D :
1. Sand fi l ters and ejectors ......... Condition 2. 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 MARGIN Procedure : 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 on the present supplement.
o Manual thermal check (on ground, in cruise, reference check) use figure 3 and 4 on the present supplement.
EASA APPROVED
E SUP.I9
ffr sl f>al
fil l\1 l'\.J i'
5 0
1 0
T = G T + A T ,10
47 ,2 - 3 , 3 = 43 ,9 -20
To be co m pa red w i th reco rded T-30
-40
60
* v 5 5
uJ f g E, o F 5 0 a a A G T tE
o 45
E ll.
6 o rq o s 3 s c) c UJ
-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 E POWER MARGIN
C H E C K
!$ 'z+
FLIGHT MANUAL
To be com pa red w i t h ac tua l TOT
,-oZ I, { I
50
2 A
1 0
lrJ
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 kt A 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
FLIGHT MANUAL
EXAMPLE : TOTc = TOTb + ATOT 850 - 7,5 = 842,5 To be compared w i t h ac tua l TOT
5 0
-20 6 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 FLIGHT IAS - 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=ts 1200q:=t
1 0000
Flgure 4
Nl = 94o/o
N R = 3 4 6 r p m 1 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 h reco rded T-30
-40
; v 5 5
UJ= g E, o F 5 0 (t) a o E, C'
45
GT
UJ
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 ENGINE POWER MARGIN
C H E C K
-l t\l n{ l\J tN t?I
$,f -+, \l
ffi#t- $
| | l'J.l l'=il-flll fi-l l't.l l'tJ l\
5 0
1 0
N1 = 98o/o
T = G T + A T
T = 4 7 , 2 ' 5 , 4 = 4 1 , 8
-10
-20
To be co m pared w i th reco rded T-30
-40
60
o c r E
o 45
E l,t-
3 4 0 tt N e o 14 o) 3 3s o a?
UJ
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 ENGINE POWER MARGIN
C H E C K
z+ l < L
FLIGHT MANUAL
5 PERFORMANCE The regulatory performances data specified in the Basic Flight Manual and in the Supplements used remain applicable and are completed or modified by the following regulatory 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)............... .22and23 r 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 and27 r 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
5.1 TWIN ENGINE HOVER PERFORMANCE
coNpr i l o [ 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 HOVER P E R F O R M A N C E I G E MAXIMUM WEIGHTS
o o o
q t! o lt o= (L q UJ o n
6 v o; @ 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 0 W E I G H T
E X A M P L E : Hp = l oooo f t
O A T = 1 0 " C W E I G H T = 4 1 0 0 k g
N
- 9
, tm 0 f l
o
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 HOVER P E R F O R M A N C E I G E MAXIMUM WEIGHTS
o o o
ul o
q CD€ t o e lrJ 3 0 0 0 3 500 4000 4500 kg 5 000
r l l
8000 r r r l l
9 0 0 0 r 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^
lO o =F--\
l.. t y '
t?_ t l
F T oI I m a x i m u m H o
1 3 0 0 0 f t
\ tll
3
s.+$- \
VJ
r SUP.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 R P E R F O R M A N C E I G E M A X I M U M W E I G H T S
o o o
l! o
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 " C W E f G H T = 4 2 4 0 k g
WND WND uREsnchrt
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 HOVER PERFORMANCE IGE MAXIMUM WEIGHTS
o o o
l! o= o.
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 C W EIG HT = 4628 kg
o) J'
F- g trj 3 U) a o G, o
a\ f ' . m a x i m u m H o 1 3 0 0 0 f t
e / I
D s
3 o
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 HOVER PERFORMANCE OGE MAXIMUM WEIGHTS
o o o
q ct) co t o c?
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 0 W E I G H T
E X A M P L E : Hp = Tooo f t
O A T = 2 O ' C W E IG HT = 4000 kg
o) .Y
I n u m H ( )00 fr I' l l
lt
F
o) ./
*Yt -
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 HOVER P E R F O R M A N C E O G E MAXIMUM WEIGHTS
o c) o
tL o= o. C" ul I
q (D @ t o a?
uJ
3000 3500 4000 4500 ( k g ) s000
7000 8000 9000 1 0 0 0 0 ( l b ) 1 1 0 0 0 W 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(').-
I I o rO @
=
FLIGHT MANUAL
5.2 CLIMB PERFORMANCE The 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 "actual weight", 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 to determine the weight faclor (Figures 13A and 1 3B).
FIGURES 13A and 138
+ F IGURES 16Aand16B l7Aand 178 18A and 188
@ w E r c H r I N D E X @ R/c
,1
llJ
t
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 T F O R D E T E R M I N I N G
R A T E O F C L I M B
o q
30 40 o A T ( ' C )
E X A M P L E : O A T = 0 o C
H p = 4 0 0 0 f t T R A N S F E R S C A L E
Flgure 13A
EASA APPROVED
C O N D I T I O N S
-
I N D E X O F W E I G H T F O R D E T E R M I N I N G
R A T E O F C L I M B
o g g o
ut 6 . 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
= $
4 2 0 0 k g I N D E X O F W E I G H T = 4 . 6 2 5
Figure 138
EASA APPROVED
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.ENGINE RATE OF CLIMB Vy
q t! o tJ- o= o- I 6
= ot€ s o a?
ul
E X A M P L E : O A T = 0 ' C
Hp = Sooo f t T R A N S F E R S C A L E = 7 . 8
Figure 14A
EASA APPROVED
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-ENGINE RATE OF CL IMB Vy
q o r4t (r) o UJ z 3 q co o (D (\l
llJ
2 000 R/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 . 5 R/C = 1234 ft/m in
Flgure 148
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-ENGINE RATE OF CLIMB Vy
o q z o o
l.t. o= E o o
= o CO t oq?
30 40 o A T ( " C )
E X A M P L E : O A T = 0 ' C
Hp = 17ooo f t T R A N S F E R S C A L E = 6 . 7
Figure 15A
EASA APPROVED
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-ENGINE RATE OF CLIMB Vy
q oro ct o lrJ z= q o o
o) s{
2 000 R/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 . 5 R/C = 1091 f t lm in
Figure 158
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 CLIMB ONE ENGINE INOPERATIVE
Vy
o A T ( ' C )
E X A M P L E : O A T = 0 o C
Hp = o f t T R A N S F E R S C A L E = 1 7 . 2
Figure 16A
EASA APPROVED
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
Vy
ol g o C? (o o UJ z 3 q @ o g)
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 . 5 R/C = 282 ft/m in
( ft /m in
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 INOPERATIVE RATE OF CLIMB Vy
o q z o q,
lr l
IrJ
dB
EXAM P LE : OAT = -5 'C
Hp = 14000 f t T R A N S F E R S C A L E = 1 7 . 4
ffi"fi:oo;
C
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 CLIMB ONE ENGINE INOPERATIVE
Vy
z= q 6 o
ul -9ffi 500 1000 1500 R/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 . 5 R/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 r L,? -Y
,I - 1 -
I I
4) / cD)
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
RATE OF CLIMB ONE ENGINE INOPERATIVE
Vy
= g)
EXAM PLE : O A T = 0 o C
H p = 9 o o o f t T R A N S F E R S C A L E = 2 1 . 0
Figure 18A
EASA APPROVED
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 IMB O N E E N G I N E I N O P E R A T I V E
Vy
= 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 . 5 R/C = 400 f t /m in
I V / 'J
I V / t/ / /
/ / / l r " I I I / / / A / 7
-7 J
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
/ / / / / IO
/ /
/ / ) A / / / / / / /
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
I I r lxeoFF wErcHTs PERMTTnNG I CLIMB AT 150 ft lmin 1000 ft I ABOVE GROUND WrrH
I oNE ENGTNE TNOPERATTVE I
o o o
3000 3500 4000 4500 5000
7000 8000 9000 1 0 0 0 0 ( r b ) 1 1 0 0 0 WEIG HT
E X A M P L E : Hp = 5ooo f t
O A T = 1 0 ' C W E I G H T = 4 1 0 0 k g
CD
l t
m a x i m u n 1 3 0 0 0 '
HC I't
.< / \
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
I I TAKEOFF WEIGHTS PERMITTING
I cuMB AT 150 frlmtn rooo ft I ABOVE GROUND WtrH I
oNE ENGTNE TNOPERATTVE
tr. o F
@ 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 0 W E I G H T
E X A M P L E : Hp = 3ooo f t
O A T = 2 0 " C W E I G H T = 4 1 4 0 k g
o, -t
o rO @
A l t i tude \ lgooo f t
f--$ I
l u
l o
\ ta\ I
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 TAKEOFF WEIGHT
2 0 0 0 0
1 5 0 0 0
o o o
so00
o s
O 3000 3500 4000 4 s 0 0 ( k g ) 5 0 0 0 (D @
3 7000 8000 9000 10000 ( l b ) 11000 a?
W E I G H T
I ot l<
o lo @ sf
I g UJ
= ,. ti
\.\ \ S -l \ l 'go
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 TAKEOFF WEIGHT
2 0 0 0 0
1 5 0 0 0
o o o
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
x
SUP.l9 o4-20 Page 35
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 - 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 TAKEOFF WEIGHT
2 0 0 0 0
1 s 0 0 0
o o o
5 0 0 0
IL o (o
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)-- o rt) co $
:) =
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
MAXIMUM TAKEOFF WEIGHT
20000
IJJ
3 0 0 0 35 00 4000 4 5 0 0 ( k g ) s 0 0 0 r l l
7000 r l l
W E I G H T
i o)
= f, =
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 LANDING WEIGHT
ON CLEAR AREA
o o o
5 0 0 0
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
- / l 5 0 ft o
= f, =
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
o o- O UJ o q (D @ tf o a?
UT 3000 3s00 4000 4500 ( xg ) 5000
7000 8000 9000 10000 ( t b ) 1 1 0 0 0
EXAM PLE: Hp = looo f t
OAT = 20" C W E I G H T = 3 9 5 0 k g
I o,
\* 3n, =:)
r.'../a! t -l
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
lrJ 3000 3500 4000 4500 ( kg ) s000
7000 8000 9000 10000 ( ] b ) 11000
EXAMPLE: Hp = 2000 f t
OAT = 20 ' C W E I G H T = 3 9 0 0 k g
o) .Y
o rJ) @ +
t l
,i, o 5
) i' '!v,u ) \. .N \ \