AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Table of Contents
SECTION 4
PERFORMANCE DATA
TABLE OF CONTENTS
Page
GENERAL ....................................................................................... 4-1
USING THE GRAPHS ..................................................................... 4-1
DENSITY ALTITUDE CHART ......................................................... 4-2
CONVERSION CHART ................................................................... 4-4
AIRSPEED CALIBRATION CURVE ............................................... 4-5
POWER ASSURANCE CHECK...................................................... 4-8
OPERATION VS ALLOWABLE WIND ......................................... 4-13
HOVER CEILING........................................................................... 4-15
HEIGHT - VELOCITY DIAGRAM .................................................. 4-20
RATE OF CLIMB........................................................................... 4-23
AUTOROTATION GLIDE DISTANCE ........................................... 4-34
NOISE CHARACTERISTICS ........................................................ 4-36
EASA Approved
Issue 1
Page 4-i
Section 4
Table of Contents
AW119 MKII G1000H RFM
Document No. 109G0040A033
LIST OF FIGURES
Page
4-1.
4-2.
Density / Altitude Chart ........................................................4-3
Conversion Chart .................................................................4-4
INSTRUMENT CALIBRATIONS
4-3.
Airspeed Calibration Curve - Pilot........................................4-6
4-4.
Airspeed Calibration Curve - ESIS.......................................4-7
ENGINE POWER CHECKS
4-5.
Power Assurance Check - Hover.........................................4-9
4-6.
Power Assurance Check - In Flight (130 KIAS) .................4-10
4-7.
Power Assurance Check - In Flight (100 KIAS) .................4-11
OPERATIONS VS ALLOWABLE WIND
4-8.
Wind/Ground Speed Azimuth Envelope (sheet of 1 of 3) ..4-13
4-8.
Wind/Ground Speed Azimuth Envelope (sheet of 2 of 2) ..4-14
HOVER CEILING
4-9.
In Ground Effect (IGE) - Take-Off Power (TOP)
(Heater Off) ........................................................................4-16
4-10. In Ground Effect (IGE) - Maximum Continuous Power
(MCP) (Heater Off).............................................................4-17
4-11. Out of Ground Effect (OGE) - Take-Off Power (TOP)
(Heater Off) ........................................................................4-18
4-12. Out of Ground Effect (OGE) - Maximum Continuous
Power (MCP) (Heater Off) .................................................4-19
HEIGHT - VELOCITY DIAGRAM
4-13. Height - Velocity Diagram - Chart A...................................4-21
4-14. Height - Velocity Diagram - Chart B...................................4-22
Page 4-ii
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Table of Contents
Page
RATE OF CLIMB
4-15. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2050 kg ..................................................... 4-24
4-16. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2250 kg ..................................................... 4-25
4-17. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2450 kg ..................................................... 4-26
4-18. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2650 kg ..................................................... 4-27
4-19. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2850 kg ..................................................... 4-28
4-20. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2050 kg ..................................................... 4-29
4-21. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2250 kg ..................................................... 4-30
4-22. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2450 kg ..................................................... 4-31
4-23. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2650 kg ..................................................... 4-32
4-24. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2850 kg ..................................................... 4-33
AUTOROTATION GLIDE DISTANCE
4-25. Autorotation Glide Distance ............................................... 4-35
EASA Approved
Issue 1
Page 4-iii
Section 4
Table of Contents
AW119 MKII G1000H RFM
Document No. 109G0040A033
LIST OF TABLES
Page
4-1.
4-2.
Hover ceiling - Correction table..........................................4-15
Rate of climb - Correction table .........................................4-23
Page 4-iv
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
SECTION 4
PERFORMANCE DATA
GENERAL
The performance data presented herein are derived from the engine
manufacturer’s minimum specification power for the engine less
installation losses.
These data are applicable to the basic helicopter without any optional
equipment which would appreciably affect lift, drag or power available.
USING THE GRAPHS
The performance information is presented graphically and on the
sequence in which it would ordinarily be used. The introduction to
each performance item contains an example of graph usage.
Additionally, each graph contains a pictogram showing the correct
sequence of steps in graph usage. As aircraft performance can be
substantially affected by many factors (weight, altitude, temperature,
power levels, etc,), careful attention should be paid to the explanatory
text accompanying each graph to assure that the correct set of factors
is being used.
When quick estimates of performance are required (no interpolation
between curves), it is recommended that the most critical curves be
used for estimates (higher weight, higher density altitude, etc.).
EASA Approved
Issue 1
Page 4-1
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
DENSITY ALTITUDE CHART
(Figure 4-1)
Enter the graph at the desired value of Outside Air Temperature
(OAT), on the horizontal axis. Proceed vertically until intercepting the
desired value of Pressure Altitude. Proceed left to read the resulting
Density Altitude (in feet). Proceed right to read the corresponding
value of the reciprocal of square root of the density ratio, which is used
to calculate True Airspeed.
Example:
At a Pressure Altitude of 5,000 ft and OAT of +25 °C, determine the
corresponding Density Altitude.
Solution:
Enter Figure 4-1 at an OAT of +25 °C, and proceed vertically until
intersecting a Pressure Altitude of 5,000 ft (diagonal curves). From
this point, proceed left to read a Density Altitude of 7,300 ft.
Page 4-2
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
▼
▼
DENSITY ALTITUDE CHART
▼
OUTSIDE AIR TEMPERATURE - [°F]
-50
10
-10
-30
30
50
90
70
110
130
1.52
1.50
1.48
1.46
1.44
1.42
1.40
1.38
1.36
1.34
1.32
1.30
1.28
1.26
1.24
1.22
1.20
1.18
1.16
1.14
1.12
0
00
24
24000
0
00
22
22000
0
00
20
20000
00
180
AR
ND
STA
18000
16000
DENSITY ALTITUDE - [ft]
0
00
14
AY
DD
14000
0
00
16
00
120
12000
0
00
10
10000
00
80
8000
00
60
6000
1.10
1.08
0
0
40
4000
1.06
00
20
2000
1.04
1.02
0
0
T
-2000
E
EE
-F
-4000
E
0.98
0
0
-40
TI
AL
0.96
0.94
00
UR
-60
S
ES
-6000
1.00
00
-20
D
TU
σ
-70
1/
26000
PR
0.92
00
-80
-8000
0.90
0.88
-10000
-60 -50 -40 -30 -20 -10
0
10
20
30
40
50
60
OUTSIDE AIR TEMPERATURE - [°C]
119G1560A001 ISSUE A
ICN-19-A-154000-G-A0126-00001-A-01-1
Figure 4-1. Density / Altitude Chart
EASA Approved
Issue 1
Page 4-3
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
CONVERSION CHART
(Figure 4-2)
The table in Figure 4-2 is self-explanatory. The conversion from Metric
System values to Imperial System values, and vice-versa, is given for
a number of useful flight parameters.
CONVERSION CHART
m
6000
ft
kg
20000
19000
5500
3000
2900
4500
15000
13000
6200
6100
2700
50
45
40
35
6000
5900
30
5800
2600
14000
4000
6400
6300
2800
5000
16000
6600
°C
6500
18000
17000
lb
5700
5500
20
2400
3500
5200
11000
3000
2300
2200
8000
7000
2100
10
5000
4000
4600
4400
4200
4000
3900
3000
1700
2000
500
1000
-5
-15
-20
3500
-30
-35
3400
0
0
ALTITUDE
1500
105
300
100
290
95
280
155
150
90
270
145
85
260
140
250
135
240
14
230
130
125
220
120
13
210
115
75
70
60
50
40
30
25
15
-40
200
190
180
170
165
160
110
105
100
95
17
16
15
3400
750
700
3000
2800
2600
550
11
2200
500
10
2000
450
9
1800
400
8
1600
7
1400
1200
130
70
120
65
110
60
100
55
50
6
45
5
1000
4
800
60
140
600
2400
140
70
160
3200
80
75
80
180
800
650
12
IMP.
Gallon
850
3600
85
90
lt
120
100
90
40
35
30
-15
50
-20
40
20
-25
30
15
-30
20
10
-35
10
5
-40
0
0
25
WEIGHT TEMPERATURE SPEED
119G1560A001 ISSUE A
18
3800
150
0
-5
170
ft/min
160
5
-10
-25
3600
1600
310
10
3800
3700
110
20
-10
4100
1800
180
175
19
320
35
0
4300
1900
330
115
45
5
4900
4800
120
55
4500
2000
6000
1000
15
4700
2000
1500
5100
5000
10000
9000
2500
5300
m/s
65
5400
12000
kts
80
25
5600
2500
km/h
°F
350
80
300
60
250
200
3
600
2
400
40
150
100
1
200
50
0
0
0
VERTICAL
VELOCITY
20
0
CAPACITY
ICN-19-A-154000-G-A0126-00002-A-01-1
Figure 4-2. Conversion Chart
Page 4-4
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
AIRSPEED CALIBRATION CURVE
(Figure 4-3 and 4-4)
Calibration curves are presented for the PFD and ESIS indicators.
The Indicated Airspeed shown on the cockpit instrument is produced
by pressure readings at the aircraft pitot and static ports and, in general, these pressure readings contain errors which must be corrected
in order to obtain Calibrated Airspeed (the airspeed which would be
shown on the cockpit instrument if there were no errors). Calibrated
airspeed must be used in order to calculate correct values of the True
Airspeed.
The magnitude of the error depends on the Indicated Airspeed. Enter
the Airspeed Calibration Curve graph (Figures 4-3), with the desired
value of Indicated Airspeed, and proceed vertically until intercepting
the curve. Proceed to the left to read the corresponding value of Calibrated Airspeed. Use this value to calculate the corresponding True
Airspeed, as required.
Example:
On the Air Data System Indication, determine the Calibrated Airspeed
corresponding to an Indicated Airspeed of 50 knots.
Solution:
Use Figure 4-3 for PFD indicator. Enter the graph at an Indicated Airspeed of 50 knots and proceed vertically until intersecting the curve.
Proceed left and read the corresponding Calibrated Airspeed of
52 knots.
EASA Approved
Issue 1
Page 4-5
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
AIRSPEED CALIBRATION CURVE
PFD INDICATOR
(FORWARD FLIGHT)
160
150
140
CALIBRATED AIRSPEED [kt]
130
120
110
100
90
80
70
60
50
40
30
20
10
0
0 10 20 30 40 50 60 70 80 90 100110120130140150160
INDICATED AIRSPEED [kt]
109G1580A035 Rev. A
ICN-19-B-154000-G-A0126-00001-A-01-1
Figure 4-3. Airspeed Calibration Curve - Pilot
Page 4-6
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
AIRSPEED CALIBRATION CURVE
ESIS INDICATOR
(FORWARD FLIGHT)
160
150
140
CALIBRATED AIRSPEED [kt]
130
120
110
100
90
80
70
60
50
40
30
20
10
0
0 10 20 30 40 50 60 70 80 90 100110120130140150160
INDICATED AIRSPEED [kt]
109G1580A035 Rev. A
ICN-19-B-154000-G-A0126-00002-A-01-1
Figure 4-4. Airspeed Calibration Curve - ESIS
EASA Approved
Issue 1
Page 4-7
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
POWER ASSURANCE CHECK
The Power Assurance Check charts indicate if the engine power
available is within the limits established for the legitimate use of the
RFM.
A power assurance check should be performed daily. Additional
checks should be made if unusual operating conditions or indications
arise. Three power assurance charts are provided, one for a hover
check and the remaining charts for a level flight check at 130 KIAS or,
if this condition is not attainable because engine MCP limits are first
encountered, at 100 KIAS. The heading of each chart contains the
procedure to be followed during the power assurance check.
The hover check is performed prior to takeoff and the in-flight check is
provided for periodic in-flight monitoring of engine performance. Either
power assurance check method may be selected at the discretion of
the pilot.
It is the pilot’s responsibility to accomplish the procedure safely,
considering passenger load, terrain being overflown and the
qualification of persons on board to assist in watching for other air
traffic and to record power check data.
If the hover check is unsuccessful, engine performance is less than
minimum specification and performance data contained in this manual
cannot be achieved.
Refer to EMM.
Page 4-8
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
POWER ASSURANCE CHECK in HOVER
HEATER OFF
GENERATOR LOAD TO MINIMUM
NR 102%
INCREASE COLLECTIVE UNTIL LIGHT ON SKID OR HOVERING AT 3 FEET. DO NOT EXCEED ITT 755°C OR N1 100.1% OR TQ 100%
STABILIZE POWER 1 MINUTE, THEN RECORD OAT, PRESSURE ALTITUDE, ENGINE TORQUE, ITT AND N1
ENTER CHART AT INDICATED TQ, MOVE DOWN TO INTERSECT PRESSURE ALTITUDE, PROCEED TO THE RIGHT TO INTERSECT OAT,
THEN MOVE UP TO READ VALUES FOR MAXIMUM ALLOWABLE ITT AND N1
IF INDICATED ITT OR N1 EXCEEDS MAXIMUM ALLOWABLE, REPEAT CHECK, STABILIZING POWER FOR THREE MINUTES
IF THE ENGINE EXCEEDS ALLOWABLE ITT OR N1 AFTER STABILIZING POWER FOR THREE MINUTES, PUBLISHED PERFORMANCE MAY NOT BE ACHIEVABLE. REFER TO EMM
NOTE: ENGINE TORQUE SHOULD BE PREFERABLY SET ABOVE 70% FOR REPEATABILITY OF THE TESTS.
ENGINE TORQUE TQ (%)
40
50
60
70
80
MAXIMUM ALLOWABLE ITT (°C)
90
100
450
500
550
600
650
700
MAXIMUM ALLOWABLE N1 (%)
750
800
80
85
90
95
100
105
50
40
30
20
10
0
- 10
- 20
- 30
- 40 )
°C
T(
OA
50
40
30
20
10
0
-10
-20
-30
-40
)
°C
T(
OA
PR
ES
SU
.
E
00
20
00
30 0
0
40
00
50 0
0
60 0
0
70 0 t )
0 f
80 T (
AL
R
10
-1
00 0 00
0
119G1560A001 ISSUE A
ICN-19-A-154000-G-A0126-00004-A-01-1
Figure 4-5. Power Assurance Check - Hover
EASA Approved
Issue 1
Page 4-9
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
POWER ASSURANCE CHECK in LEVEL FLIGHT
130 KIAS
ESTABLISH LEVEL FLIGHT ABOVE 1000 FT AGL
HEATER OFF
GENERATOR LOAD TO MINIMUM
NR 102%
STABILIZE A 130 KIAS LEVEL FLIGHT WITHOUT EXCEEDING TQ 100%, ITT 755°C OR N1 100.1%.
NOTE: IF 130 KIAS CAN NOT BE REACHED DUE TO ATMOSPHERIC CONDITIONS OR ENGINE LIMITATIONS, THEN LEVEL FLIGHT CAN BE ESTABLISHED AT 100 KIAS (REFER TO NEXT CHART).
STABILIZE POWER 1 MINUTE, THEN RECORD OAT, PRESSURE ALTITUDE, ENGINE TORQUE, ITT AND N1
ENTER CHART AT INDICATED TQ, MOVE DOWN TO INTERSECT PRESSURE ALTITUDE, PROCEED TO THE RIGHT TO INTERSECT OAT,
THEN MOVE UP TO READ VALUES FOR MAXIMUM ALLOWABLE ITT AND N1
IF INDICATED ITT OR N1 EXCEEDS MAXIMUM ALLOWABLE, REPEAT CHECK, STABILIZING POWER FOR THREE MINUTES
IF THE ENGINE EXCEEDS ALLOWABLE ITT OR N1 AFTER STABILIZING FOR THREE MINUTES, CARRY OUT A POWER ASSURANCE CHECK IN HOVER.
ENGINE TORQUE TQ (%)
40
50
60
70
80
MAXIMUM ALLOWABLE ITT (°C)
90
100
500
600
700
MAXIMUM ALLOWABLE N1 (%)
800
80
85
90
95
100
105
50
40
30
20
10
0
-10
-20
-3 0
- 4 0 ° C)
T(
OA
50
40
30
20
10
0
- 10
-2 0
- 30
- 40 ° C )
T(
OA
PR
00
20
00
30
00
40
00
50 0
0
60 0
0
70
00
80 0
0
ft)
90 0 T .(
00 L
10 E A
R
SU
ES
10
00 0
-1
00
0
119G1560A001 ISSUE A
ICN-19-A-154000-G-A0126-00005-A-01-1
Figure 4-6. Power Assurance Check - In Flight (130 KIAS)
Page 4-10
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
POWER ASSURANCE CHECK in LEVEL FLIGHT
100 KIAS
ESTABLISH LEVEL FLIGHT ABOVE 1000 FT AGL
HEATER OFF
GENERATOR LOAD TO MINIMUM
NR 102%
STABILIZE A 100 KIAS LEVEL FLIGHT WITHOUT EXCEEDING TQ 100%, ITT 755°C OR N1 100.1%.
STABILIZE POWER 1 MINUTE, THEN RECORD OAT, PRESSURE ALTITUDE, ENGINE TORQUE, ITT AND N1
ENTER CHART AT INDICATED TQ, MOVE DOWN TO INTERSECT PRESSURE ALTITUDE, PROCEED TO THE RIGHT TO INTERSECT OAT,
THEN MOVE UP TO READ VALUES FOR MAXIMUM ALLOWABLE ITT AND N1
IF INDICATED ITT OR N1 EXCEEDS MAXIMUM ALLOWABLE, REPEAT CHECK, STABILIZING POWER FOR THREE MINUTES.
IF THE ENGINE EXCEEDS ALLOWABLE ITT OR N1 AFTER STABILIZING POWER FOR THREE MINUTES, CARRY OUT A POWER ASSURANCE CHECK IN HOVER
ENGINE TORQUE TQ (%)
40
50
60
70
MAXIMUM ALLOWABLE ITT (°C)
80
90
100
500
600
700
MAXIMUM ALLOWABLE N1 (%)
800
80
85
90
95
100
105
50
40
30
20
10
0
-10
-20
-3 0
- 4 0 ° C)
T(
OA
50
40
30
20
10
0
- 10
-2 0
- 30
- 40 C )
°
T(
OA
PR
ES
00
20
00
30
00
40 0
0
50
00
60 0
0
70
00
80 0
0
)
9 0 0 0 . (f t
0 LT
10 A
RE
SU
10
00 0
-1
00
0
119G1560A001 ISSUE A
ICN-19-A-154000-G-A0126-00006-A-01-1
Figure 4-7. Power Assurance Check - In Flight (100 KIAS)
EASA Approved
Issue 1
Page 4-11
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
This Page Intentionally Left Blank
Page 4-12
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
OPERATION VS ALLOWABLE WIND
(Figure 4-8)
Satisfactory stability and control was demonstrated for sideways and
rearward flight up to the maximum weight, in hover IGE or OGE in the
following wind/ground speed azimuth envelope.
350°
0°
10°
315°
45°
DIRECTION
OF WIND
60°
DIRECTION
OF WIND
15 20
270°
35
DIRECTION
OF WIND
GS/WIND
VELOCITY
40 45 50 (kts)
90°
DIRECTION
OF WIND
225°
135°
180°
160°
APPLICABILITY: UP TO 3000 ft Hd
OPERATION WITH PASSENGER CABIN DOORS CLOSED
OPERATION WITH ONE OR BOTH PASSENGER
CABIN DOORS OPEN OR REMOVED
109G0290T149/2 ISSUE A
ICN-19-A-154000-G-A0126-00007-A-01-1
Figure 4-8. Wind/Ground Speed Azimuth Envelope (sheet 1 of 2).
EASA Approved
Issue 1
Page 4-13
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
350°
0°
10°
315°
45°
DIRECTION
OF WIND
60°
DIRECTION
OF WIND
20
270°
GS/WIND
VELOCITY
45 (kts)
30 35 40
90°
DIRECTION
OF WIND
DIRECTION
OF WIND
225°
135°
180°
160°
APPLICABILITY: FROM 3000 TO 8700 ft Hd
OPERATION WITH PASSENGER CABIN DOORS CLOSED
OPERATION WITH ONE OR BOTH PASSENGER
CABIN DOORS OPEN OR REMOVED
109G0290T149/2 ISSUE A
ICN-19-A-154000-G-A0126-00008-A-01-1
Figure 4-8. Wind/Ground Speed Azimuth Envelope (sheet 2 of 2).
Page 4-14
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
HOVER CEILING
(Figures 4-9 thru 4-12)
The Hover Ceiling charts define the maximum weight at which an In
Ground Effect (IGE) hover (3 ft skid height AGL) or an Out of Ground
Effect (OGE) hover (at least 60 ft skid height AGL) is possible for
different combinations of Pressure Altitude and OAT with main rotor
speed (NR) at 102% and zero wind conditions.
The performance presented for Take-Off Power (TOP) and for
Maximum Continuous Power (MCP) refer to an electrical load of 100 A.
When the electrical load is greater than 100 A, reduce the maximum
weight obtained from the charts according to Table 4-1.
Table 4-1. Hover ceiling - Correction table
WHEN ELECTRICAL LOAD > 100 A REDUCE GROSS WEIGHT BY [KG]:
0
0
0
0
0
0
0
0
0
0
0
10
0
15
0
15
10
40
10
35
25
50
20
40
40
55
35
50
45
65
40
65
50
70
45
70
85
85
75
80
119G1560A001 ISSUE A
EASA Approved
ICN-19-A-154100-G-A0126-00005-A-01-1
Issue 1
Page 4-15
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
HOVER CEILING IN GROUND EFFECT
TAKE-OFF POWER
▲
ROTOR SPEED:102%
ZERO WIND
ELECTRICAL LOAD: 100 A
SKID HEIGHT: 3 ft
▲
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
15
43
GROSS WEIGHT [lb x 100]
47
51
55
59
14
-2
ft
0
0
15
MA
XO
8
20
30
30
25
AT
7
LIM
20
IT
PRESSURE ALTITUDE [ft x 1000]
PERFORMANCE ABOVE
15000 ft DENSITY ALTITUDE
ARE CALCULATED
9
35
10
11
10
40
0
00
12
45
0
-1
HD
13
63
-3 35
0
6
5
15
40
4
PRESSURE ALTITUDE [m x 100]
39
10
3
2
5
1
OAT - [°C]
0
0
-1
17
18
19
20
119G1560A001 ISSUE A
21 22 23 24 25 26 27
GROSS WEIGHT [kg x 100]
28
29
30
ICN-19-A-154100-G-A0126-00001-A-01-1
Figure 4-9. In Ground Effect (IGE) - Take-Off Power (TOP)
(Heater Off)
Page 4-16
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
HOVER CEILING IN GROUND EFFECT
MAXIMUM CONTINUOUS POWER
ROTOR SPEED:102%
ZERO WIND
ELECTRICAL LOAD: 100 A
SKID HEIGHT: 3 ft
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
39
15
GROSS WEIGHT [lb x 100]
47
51
55
59
43
63
45
14
13
00
ft
-3 -35
0
-2
0
HD
12
40
-1
0
15
0
0
35
9
20
25
OAT
8
30
6
20
30
IT
LIM
7
5
15
4
3
10
PERFORMANCE ABOVE
15000 ft DENSITY ALTITUDE
ARE CALCULATED
40
2
PRESSURE ALTITUDE [m x 100]
10
10
MAX
PRESSURE ALTITUDE [ft x 1000]
11
5
1
OAT - [°C]
0
0
50
-1
17
18
19
20
119G1560A001 ISSUE A
21 22 23 24 25 26 27
GROSS WEIGHT [kg x 100]
28
29
30
ICN-19-A-154100-G-A0126-00002-A-01-1
Figure 4-10. In Ground Effect (IGE) - Maximum Continuous
Power (MCP) (Heater Off)
EASA Approved
Issue 1
Page 4-17
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
HOVER CEILING OUT OF GROUND EFFECT
TAKE-OFF POWER
▲
ROTOR SPEED:102%
ZERO WIND
ELECTRICAL LOAD: 100 A
▲
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
39
15
43
GROSS WEIGHT [lb x 100]
47
51
55
59
63
45
D
14
tH
13
-2
0f
0
00
12
40
-1
15
0
35
30
10
10
9
20
MA
25
AT
XO
8
30
20
IT
LIM
7
6
5
15
4
PERFORMANCE ABOVE
15000 ft DENSITY ALTITUDE
ARE CALCULATED
10
40
3
PRESSURE ALTITUDE [m x 100]
0
11
PRESSURE ALTITUDE [ft x 1000]
-3 35
0
2
5
1
OAT - [°C]
0
0
50
-1
17
18
19
20
119G1560A001 ISSUE A
21 22 23 24 25 26 27
GROSS WEIGHT [kg x 100]
28
29
30
ICN-19-A-154100-G-A0126-00003-A-01-1
Figure 4-11. Out of Ground Effect (OGE) - Take-Off Power (TOP)
(Heater Off)
Page 4-18
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
HOVER CEILING OUT OF GROUND EFFECT
MAXIMUM CONTINUOUS POWER
ROTOR SPEED:102%
ZERO WIND
ELECTRICAL LOAD: 100 A
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
39
15
43
GROSS WEIGHT [lb x 100]
47
51
55
59
63
45
14
13
0
ft
OAT - [°C]
HD
0
-2
1
12
40
-3 35
0
0
50
30
9
10
25
8
20
OAT
7
20
5
30
LIMIT
6
15
4
10
3
40
2
1
PRESSURE ALTITUDE [m x 100]
0
0
10
MAX
PRESSURE ALTITUDE [ft x 1000]
35
-1
11
5
PERFORMANCE ABOVE
15000 ft DENSITY ALTITUDE
ARE CALCULATED
0
0
50
-1
17
18
19
20
119G1560A001 ISSUE A
21 22 23 24 25 26 27
GROSS WEIGHT [kg x 100]
28
29
30
ICN-19-A-154100-G-A0126-00004-A-01-1
Figure 4-12. Out of Ground Effect (OGE) - Maximum Continuous
Power (MCP) (Heater Off)
EASA Approved
Issue 1
Page 4-19
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
HEIGHT - VELOCITY DIAGRAM
(Figures 4-13 and 4-14)
The Height-Velocity diagram defines the combination of airspeed and
height above ground from which a safe landing on a smooth, level and
hard surface cannot be assured following an engine failure.
The Height-Velocity diagram is valid up to the maximum GW of
2850 kg.
Two Height-Velocity charts are provided:
— CHART A is applicable up to 3,000 ft Hd;
— CHART B is applicable from 3,000 to 7,000 ft Hd.
Page 4-20
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
HEIGHT-VELOCITY DIAGRAM
FOR SMOOTH, LEVEL, HARD SURFACES
Chart A
APPLICABILITY: UP TO 3000 ft Hd
900
260
H- V
A= 5ft - 0kts
B= 10ft - 30kts
C= 60ft - 42kts
D=100ft - 50kts
E=150ft - 55kts
F=450ft - 35kts
G=750ft - 0kts
800
G
700
240
220
200
180
160
500
140
F
400
120
SKID HEIGHT - [m]
SKID HEIGHT - [ft]
600
100
300
80
AVOID OPERATION
IN THIS AREA
200
60
E
40
D
100
C
0
B
A
0
20
10
0
20
30
40
50
INDICATED AIRSPEED - [kts]
109G0290T149/2 ISSUE A
60
70
ICN-19-A-154200-G-A0126-00001-A-01-1
Figure 4-13. Height - Velocity Diagram - Chart A
EASA Approved
Issue 1
Page 4-21
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
HEIGHT-VELOCITY DIAGRAM
FOR SMOOTH, LEVEL, HARD SURFACES
Chart B
APPLICABILITY: from 3000 TO 7000 ft Hd
G
260
H- V
A= 5ft - 0kts
B= 10ft - 30kts
C= 60ft - 58kts
D=100ft - 65kts
E=150ft - 67kts
F=450ft - 47kts
G=900ft - 0kts
800
700
240
220
200
SKID HEIGHT - [ft]
600
180
160
500
140
F
400
120
SKID HEIGHT - [m]
900
100
300
80
AVOID OPERATION
IN THIS AREA
200
60
E
40
D
100
C
0
A
0
20
B
10
0
20
30
40
50
INDICATED AIRSPEED - [kts]
109G0290T149/2 ISSUE A
60
70
ICN-19-A-154200-G-A0126-00002-A-01-1
Figure 4-14. Height - Velocity Diagram - Chart B
Page 4-22
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
RATE OF CLIMB
(Figures 4-15 thru 4-24)
The Rate Of Climb (ROC) charts are presented for Take-Off Power
(TOP) rating and for Maximum Continuous Power (MCP) rating, both
with NR at 102%.
They refer to the best Rate of Climb airspeed Vy of 60 KIAS up to
15,000 ft Hp.
The performance presented for Take-Off Power (TOP) and for
Maximum Continuous Power (MCP) refer to an electrical load of 100 A.
When the electrical load is greater than 100 A, reduce the maximum
Rate of Climb obtained from the charts according to Table 4-2.
Table 4-2. Rate of climb - Correction table
WHEN ELECTRICAL LOAD > 100 A REDUCE RATE OF CLIMB BY [ft/min]:
0
119G1560A001 ISSUE A
EASA Approved
0
0
5
0
15
0
25
15
55
45
70
55
80
60
110
65
110
80
115
ICN-19-A-154300-G-A0126-00011-A-01-1
Issue 1
Page 4-23
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
RATE OF CLIMB
TAKE-OFF POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
0
2
4
RATE OF CLIMB [m/s]
6
8
10
12
14
GROSS WEIGHT
2050 kg
( 4519 lb)
14
13
40
12
35
-35
-30
-20
-10
0
10
20
11
10
30
9
MAX
LIMIT
7
25
30
8
OAT
6
20
5
15
4
40
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00001-A-01-1
Figure 4-15. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2050 kg
Page 4-24
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
RATE OF CLIMB
TAKE-OFF POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
2
4
RATE OF CLIMB [m/s]
6
8
10
12
14
GROSS WEIGHT
2250 kg
( 4960 lb)
14
13
40
12
35
-35
-30
-20
-10
0
10
20
11
10
30
9
8
OAT
7
25
30
MAX
20
LIMIT
6
5
15
4
40
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
0
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00002-A-01-1
Figure 4-16. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2250 kg
EASA Approved
Issue 1
Page 4-25
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
RATE OF CLIMB
TAKE-OFF POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
2
4
RATE OF CLIMB [m/s]
6
8
10
12
14
GROSS WEIGHT
2450 kg
( 5401 lb)
14
13
40
12
35
-35
-30
-20
-10
0
10
20
11
10
30
9
25
OAT
7
30
8
MAX
6
20
LIMIT
5
4
15
40
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
0
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00003-A-01-1
Figure 4-17. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2450 kg
Page 4-26
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
RATE OF CLIMB
TAKE-OFF POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
2
RATE OF CLIMB [m/s]
6
8
10
4
12
14
GROSS WEIGHT
2650 kg
( 5842 lb)
14
13
40
12
35
-35
-30
-20
-10
0
10
20
11
10
30
9
25
8
30
MAX
OAT
7
20
LIM
6
IT
5
15
4
40
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
0
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00004-A-01-1
Figure 4-18. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2650 kg
EASA Approved
Issue 1
Page 4-27
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
RATE OF CLIMB
TAKE-OFF POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
2
4
RATE OF CLIMB [m/s]
6
8
10
12
14
GROSS WEIGHT
2850 kg
( 6283 lb)
14
13
40
12
35
0
-35
-30
-20
-10
10
20
11
10
30
9
25
XO
8
30
MA
7
AT
20
LIM
6
IT
5
15
4
40
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
0
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00005-A-01-1
Figure 4-19. Take-Off Power (TOP) (Heater Off)
- Gross Weight 2850 kg
Page 4-28
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
RATE OF CLIMB
MAXIMUM CONTINUOUS POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
2
RATE OF CLIMB [m/s]
6
8
10
4
12
14
GROSS WEIGHT
2050 kg
( 4519 lb)
14
13
40
12
35
-35
-30
-20
-10
0
10
20
11
10
30
9
6
LIMIT
8
25
30
7
MAX OAT
20
5
15
4
40
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
0
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00006-A-01-1
Figure 4-20. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2050 kg
EASA Approved
Issue 1
Page 4-29
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
RATE OF CLIMB
MAXIMUM CONTINUOUS POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
2
RATE OF CLIMB [m/s]
6
8
10
4
12
14
GROSS WEIGHT
2250 kg
( 4960 lb)
14
13
40
12
35
0
-35
-30
-20
-10
10
20
11
10
30
9
8
7
20
MIT
6
25
30
MAX OAT LI
5
15
4
40
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
0
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00007-A-01-1
Figure 4-21. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2250 kg
Page 4-30
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
RATE OF CLIMB
MAXIMUM CONTINUOUS POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
2
4
RATE OF CLIMB [m/s]
6
8
10
12
14
GROSS WEIGHT
2450 kg
( 5401 lb)
14
13
40
12
35
-350
-3
-20
-10
0
10
20
11
10
30
9
MAX O
25
30
8
AT LIM
7
6
20
IT
5
15
4
40
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
0
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00008-A-01-1
Figure 4-22. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2450 kg
EASA Approved
Issue 1
Page 4-31
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
RATE OF CLIMB
MAXIMUM CONTINUOUS POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
2
RATE OF CLIMB [m/s]
6
8
10
4
12
14
GROSS WEIGHT
2650 kg
( 5842 lb)
14
13
40
12
35
-35
-30
-20
-10
0
10
20
11
10
30
9
MAX
25
30
8
OAT
7
LIMIT
6
20
5
15
4
40
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
0
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00009-A-01-1
Figure 4-23. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2650 kg
Page 4-32
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
RATE OF CLIMB
MAXIMUM CONTINUOUS POWER
ROTOR SPEED: 102%
ELECTRICAL LOAD: 100 A
Vy: 60 KIAS
WITH ELECTRICAL LOAD IN EXCESS OF 100 A REFER TO CORRECTION TABLE
2
4
RATE OF CLIMB [m/s]
6
8
10
12
14
GROSS WEIGHT
2850 kg
( 6283 lb)
14
13
40
12
35
-35
-30
-20
-10
0
10
11
10
30
20
9
25
8
30
7
20
MAX O
6
5
IT
4
15
40
AT LIM
PRESSURE ALTITUDE [ft x 1000]
45
PRESSURE ALTITUDE [m x 100]
15
0
10
3
2
5
1
-1
0
50
0
0
2
4
6
119G1560A001 ISSUE A
8 10 12 14 16 18 20
RATE OF CLIMB [ft/min x 100]
22
24
26
28
ICN-19-A-154300-G-A0126-00010-A-01-1
Figure 4-24. Maximum Continuos Power (MCP) (Heater Off)
- Gross Weight 2850 kg
EASA Approved
Issue 1
Page 4-33
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
AUTOROTATION GLIDE DISTANCE
(Figure 4-25)
The autorotation glide distance chart presents the autorotation glide
distance as function of altitude, at 100% NR and is applicable to all
GW.
Page 4-34
Issue 1
EASA Approved
AW119 MKII G1000H RFM
Document No. 109G0040A033
Section 4
Performance Data
AUTOROTATION GLIDE DISTANCE
DISTANCE OVER GROUND - km
5
15
10
15 0
20
45
14
13
12
35
11
10
30
9
25
8
Maximum Glide Distance
Airspeed 100 KIAS
7
20
6
5
15
4
10
3
2
PRESSURE ALTITUDE - METERS X 100
PRESSURE ALTITUDE - FEET x 1000
40
Minimum Rate of Descent
Airspeed 70 KIAS
5
1
0
0
1
2
109G1580A035 Rev. A
3
4
5
6
7
8
9
DISTANCE OVER GROUND - nm
10
11
0
12
ICN-19-B-154300-G-A0126-00001-A-01-1
Figure 4-25. Autorotation Glide Distance
EASA Approved
Issue 1
Page 4-35
Section 4
Performance Data
AW119 MKII G1000H RFM
Document No. 109G0040A033
NOISE CHARACTERISTICS
The following noise level complies with ICAO Annex 16, Chapter 8,
4th Edition:
Model: AW119 MKII
Engine Pratt & Whitney PT6B-37A
Maximum Gross Weight 2850 kg
Configuration
Level Flyover
EPNL
(EPNdB)
Take-off
EPNL
(EPNdB)
Approach
EPNL
(EPNdB)
Clean aircraft.
No external kit
installed
88.2
90.8
91.0
Page 4-36
Issue 1
EASA Approved