Australian Government
Civil Aviation Safety Authority
TRAINING & EXAMINATION WORKBOOK
for
DAY VFR SYLLABUS
Version 3 - 01 July 2011
[formerly titled VFR (Day) Work Booklet]
The Civil Aviation Safety Authority (CASA) owns copyright of this workbook.
The workbook is only for use in training to the Day VFR aeronautical knowledge
syllabus of training and the associated CASA PPL and CPL examinations, and not
to be used for any other purpose.
After use in a CASA PPL or CPL examination, the workbook must not be removed
from the examination room but left with the CASA CyberExams supervisor for
destruction. Failure to comply with these instructions may give CASA grounds for
taking action against the candidate under CAR 298A, which action could lead to the
outcome indicated in CAR 298A (5).
CONTENTS – 2
TABLE OF CONTENTS
CONTENT
PAGE
Company Policy
Figs 1 / 2 : Aerodrome Markers/Markings
Scribble pad
Fig 3 - Take-off Weight Chart
Fig 4 - Landing Distance Chart
Fig 5 - Take-off Weight Chart
Fig 6 - Landing Chart
Loading System Alpha: Instructions
Fig 7 - Loading System Alpha
Loading System Bravo: Instructions
Fig 8 - Loading System Bravo
Loading System Charlie: Instructions
Loading System Charlie: Index Units
Fig 9 - Loading System Charlie
Scribble pad
Loading System Echo: Instructions
Loading System Echo: Instructions
(Continued)
Fig 10 - Loading System Echo: Index Units
Fig 11 - Loading System Echo:
CG Envelope
Fig 12 - Take-off Weight Chart:
Aircraft Echo
Fig 13 - Landing Weight Chart:
Aircraft Echo
Helicopter Figures “A” and “B”
Helicopter Figures “C” and “D”
Helicopter Figures “E” and “F”
WAC Extract: (3219) TOWNSVILLE
WAC Extract: (3456) SYDNEY
WAC Extract: (3356) BOURKE
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28 & 29
30
CONTENT
Figs 16 / 17 / 18: Navigation
Figs 19 / 20 / 21: Navigation
Figs 22 / 23 / 24: Navigation
Figs 25 / 26 / 27: Navigation
Figs 28 / 29 / 29A: Navigation
Figs 30 / 31: Navigation
Figs 32 / 33 / 34: Navigation
Figs 35 / 36 / 37: Navigation
Figs 38 / 39: Navigation
Figs 40 / 41 / 42 / 43: Principles of Flight
Scribble pad
Scribble pad
Scribble pad
Figs 48 / 49 Meteorology
MSL Analysis charts
Meteorology – ARFOR No. 1
Meteorology – ARFOR No. 2
Meteorology – ARFOR No. 3
Meteorology – ARFOR No. 4
Meteorology – ARFOR No. 5
Meteorology – ARFOR No. 6
Scribble pad
Scribble pad
Scribble pad
Meteorology - PCA
ARFOR Boundaries for Flights
Scribble pad
Scribble pad
PAGE
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
Pages 27 to 30, WAC Extracts.
This work contains aeronautical information and data which is © Airservices Australia 2011. No part of
this work may be reproduced in any form or by any means without the prior written consent of
Airservices Australia. Airservices Australia does not guarantee that the aeronautical information and data
is current or free from errors, and disclaims all warranties in relation to its quality, performance or
suitability for any purpose. Not for operational use. All rights reserved.
COMPANY POLICY – 3
EXTRACT FROM COMPANY OPERATIONS MANUAL
Fuel Reserves
Fuel Reserves (for all flights) shall be carried in accordance with Civil Aviation Advisory Publication,
CAAP 234-1 (1) dated November 2006.
Aeroplane Landing Areas
Selection of and operation into landing areas other than licensed aerodromes, shall be in accordance with
Civil Aviation Advisory Publication, CAAP 92-1 (1) dated July 1992.
Helicopter Landing Sites
Selection of and operations into helicopter landing sites (HLS), which are not licensed aerodromes, shall
be in accordance with the Civil Aviation Advisory Publication, CAAP 92-2 (1) dated January 1996.
AIR LAW – 4
(i)
(ii)
AERODROME
MARKERS
AERODROME
MARKINGS
Figure 1
Figure 2
(i)
(ii)
(iii)
(iii)
(iv)
(iv)
SCRIBBLE PAD – 5
PERFORMANCE & LOADING – 6
TAKE-OFF WEIGHT CHART
Figure 3
LEVEL
2
2
UP
4
1500
1400
1300
1200
1100
1000
DOWN
900
800
700
600
500
400
8000
6000
START
HERE
4000
2000
SL
40 30 20 10 0 -10
SHADE
TEMP
C
LONG WET GRASS SURFACE
LONG DRY OR SHORT WET GRASS SURFACE
REFERENCE LINE SHORT DRY GRASS SURFACE
1090 KG
1100
(B)
HEAD
TAKE-OFF WEIGHT - KG
AIRFIELD PRESSURE HEIGHT - FT
TAKE-OFF DISTANCE AVAILABLE - METRES
SLOPE PERCENT
1050
(A)
1000
5
0
10
20
950
900
TAIL
850
AMBIENT WIND COMPONENT - KNOTS
NOTES:
(1) THE GROSS WEIGHT AT TAKE-OFF SHALL
NOT EXCEED THE LESSOR OF (A) AND (B).
(2) THE MAXIMUM TAKE-OFF WEIGHT = 1090 KG
POWER TO BE USED
FLAP SETTING
TAKE-OFF SAFETY SPEED
TAKE-OFF DISTANCE FACTOR
FULL THROTTLE
10 DEGREES
60 KIAS
1.15
CLIMB LIMIT WEIGHT - KG
20
30
SHADE TEMPERATURE C
10
S.L.
40
2000
4000
6000
50
2
2
4
SLOPE PERCENT
0
REFERENCE LINE
0
4000
AIRFIELD PRESSURE
HEIGHT - FEET
5000
6
0
10
20
200
300
400
500
600
700
800
900
1000
FLAP SETTING
40 DEGREES
APPROACH SPEED
65 KT IAS
LANDING DISTANCE FACTOR 1.15
AMBIENT WIND
COMPONENT - KT
5
REFERENCE LINE
-10
1050
1055
MAX
1000
NOTE:
LANDING WEIGHT MUST
6000 NOT EXCEED CLIMB
WEIGHT LIMIT BELOW
PERFORMANCE & LOADING – 7
LANDING DISTANCE CHART
Figure 4
NOTE:
LANDING DISTANCE REQUIRED
IS INDEPENDENT OF LANDING
WEIGHT.
LANDING DISTANCE REQUIRED - METRES
CLIMB LIMIT WEIGHT - KG
20
30
40
SHADE TEMPERATURE C
10
0
2
2
4
SLOPE PERCENT
0
REFERENCE LINE
0
0
10
20
AMBIENT WIND
COMPONENT - KT
6 5 0
REFERENCE LINE
-10
200
00
40
00
60
LONG WET GRASS
SURFACE
SHORT WET OR LONG DRY GRASS
SHORT DRY GRASS
REFERENCE LINE HARD SEALED SURFACE
AIRFIELD PRESSURE HEIGHT - FEET
1055
1000
950
900
60
850
50
00
40
00
TAKE-OFF WEIGHT - KG
TAKE-OFF WEIGHT CHART
Figure 5
1050
1000
1000
950
950
900
900
850
850
800
800
750
750
TAKE-OFF WEIGHT - KG
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
1055
1050
00
NOTE:
TAKEOFF WEIGHT MUST NOT EXCEED
CLIMB WEIGHT LIMIT BELOW
ZERO
FLAP SETTING
64 KT IAS
TAKEOFF SAFETY SPEED
FULL THROTTLE
POWER SETTING
NOT LESS THAN 2350
RPM
1.15
CHART DISTANCE FACTOR
PERFORMANCE & LOADING – 8
TAKE-OFF DISTANCE AVAILABLE - METRES
1055
PERFORMANCE & LOADING – 9
LANDING DISTANCE REQUIRED - METRES
LANDING CHART
Figure 6
SLOPE PERCENT
2
LEVEL
2
DOWN
4
650
600
550
500
UP
450
0
10
20
5
TAIL
HEAD
AMBIENT WIND COMPONENT - KNOTS
400
8000
6000
4000
40
2000
SL
SHADE
TEMP
C
30 20
10
0 -10
AIRFIELD PRESSURE HEIGHT - FT
AIRFIELD PRESSURE HEIGHT - FT
CLIMB WEIGHT LIMIT
8000
1080
KG
6000
4000
2000
800
(A)
900
1000
1100
LANDING WEIGHT - KG
NOTES:
(1) THE GROSS WEIGHT AT LANDING SHALL
NOT EXCEED (A).
(2)
LANDING DISTANCE REQUIRED DOES NOT
VARY SIGNIFICANTLY WITH WEIGHT
FLAP SETTING
APPROACH SPEED
LANDING DISTANCE FACTOR
30 DEGREES
58 KIAS
1.15
PERFORMANCE & LOADING – 10
LOADING SYSTEM ALPHA
CONFIGURATION: 6/7 SEATS
INSTRUCTIONS FOR USE OF LOADING SYSTEM
1
Obtain Basic Empty Weight and Index Units from current Section of 6.2 of Flight Manual.
2
Mark Basic Empty Weight Index Units on top scale. Enter Basic Empty Weight at top of righthand column.
3
Enter weights of load items required for flight in appropriate squares of right-hand column.
Maximum weights for load items are indicated on Index Unit scales.
4
Total weights in right-hand column to obtain Zero Fuel Weight and Take-Off Weight. **
5
Draw horizontal lines on CG Envelope graph corresponding to Zero Fuel Weight and Take-Off
Weight.
6
Draw a line vertically down from point marked on Basic Empty Weight Index Units scale to first
load item scale.
* Move to the left or right on this load item index scale as per arrow directions, and mark point as
appropriate to the load indicated in the right-hand column.
(e.g. 154 KG load @ 77 KG/div. = 2 div.).
7
Draw a line vertically down from the point marked on the first load item index scale to the second
load item index scale and continue as per * above. Continue down the scales to “Rear Baggage”.
Draw a line vertically from the “Rear Baggage” point down to intersect the Zero Fuel Weight line
and Take-Off Weight line previously marked on the CG envelope graph.
8
The two intersection points as per 7, above must not exceed the boundaries of the CG envelope
graph. If they do, re-organise the load in the aircraft and start again with steps 3 to 7.
**
DO NOT EXCEED MAXIMUM TAKE-OFF WEIGHT AS SHOWN ON CG ENVELOPE
DIAGRAM OF THIS LOADING SYSTEM.
_____________________________________________________
EXAMPLE:
Basic Empty Weight
Empty Index units
Row 1
Row 2 (forward facing)
Row 3
Nose baggage
Rear baggage
Fuel
Note:
1050 KG
-260
150 KG (2 persons)
160 KG (2 persons)
120 KG (2 persons)
40 KG ----------------- Zero Fuel Wt = 1520 KG
Nil
113 KG ---------------- Take-Off Wt = 1633 KG
Basic Empty Weight includes unusable fuel and full oil.
PERFORMANCE & LOADING – 11
LOADING SYSTEM ALPHA
Figure 7
EXAMPLE
-400
-300
AIRCRAFT BASIC INDEX UNITS
-200
-100
0
+100
+200
WEIGHT (KG)
50 KG/DIV
ROW 1
OCCS
ROW 2
OCCS
ROW 2
OCCS
77 KG/DIV
50 KG/DIV
(FORWARD FACING)
77 KG/DIV
50 KG/DIV
(AFT FACING)
77 KG/DIV
50 KG/DIV
ROW 3
OCCS
77 KG/DIV
10 KG/DIV
(45 KG MAXIMUM)
NOSE
BAGGAGE
10 KG/DIV
(45 KG MAXIMUM)
REAR
BAGGAGE
ZERO FUEL WEIGHT
FUEL
(MAXIMUM 356 LITRES 252 KG)
1633 KG
MAXIMUM TAKE-OFF WEIGHT
NIL SCALE
TAKEOFF WEIGHT
1633 KG
1600 KG
1500 KG
1400 KG
1300 KG
GROSS WEIGHT (KG)
1200 KG
1100 KG
PERFORMANCE & LOADING – 12
LOADING SYSTEM BRAVO
CONFIGURATION: 4 SEATS
INSTRUCTIONS FOR USE OF LOADING SYSTEM
To check the loading of the aircraft before take-off, calculate the total weight and total moments as shown
in the example below.
Plot the total weight and moment on the “Centre of Gravity Envelope” chart, and if the intersection point
is within the envelope, the loading is acceptable.
AIRCRAFT LIMITATIONS
Maximum take-off weight
Normal category:
Utility category:
1000 KG / 2200 lbs
841 KG / 1850 lbs
Maximum baggage compartment baggage: 53 KG / 120 lbs
Notes:
1
2
3
The aircraft is fitted with standard tanks (37 US Gallons at 6 lbs / gallon)
Empty weight includes unusable fuel and undrainable oil
Obtain Moment / 1000 inch pounds from the loading graph
_____________________________________________________
EXAMPLE:
Empty weight
Oil
Fuel (141 litres)
Pilot & Co-Pilot
Rear seat passengers
Baggage
Take-Off Weight
WEIGHT (LBS)
1260
15
222
320
350
25
ARM (IN)
80
32
91
91
126
151
2192
Check CG is within the envelope
MOMENT/1000 IN LB
100.80
.48
20.02
29.12
44.10
3.78
198.30
PERFORMANCE & LOADING – 13
LOADING SYSTEM BRAVO
Figure 8
Add weight of items to be carried to aeroplane licensed
empty weight. Add moment/1000 of items to be carried
to total aeroplane moment/1000. Use Centre of Gravity
Envelope to determine acceptibility.
LOAD - WEIGHT IN POUNDS
500
LOADING GRAPH
PILOT AND COPILOT
400
CARGO
STD FUEL (37 gal. useable - 6 lbs/gal.)
OPT FUEL (51 gal. useable - 6 lbs/gal.)
300
REAR SEAT PASSENGERS
200
100
BAGGAGE
0
0
5
10
15
20
25
30
35
40
45
200
210
MOMENT/1000 INCH POUNDS
LOADING GRAPH
CENTRE OF GRAVITY ENVELOPE
CA
TE
GO
RY
2100
NO
RM
A
L
2000
1900
CA
TE
G
OR
Y
1800
1700
UT
IL
IT
Y
LOADED AIRCRAFT WEIGHT IN POUNDS
2200
1600
1500
1400
120
130
140
150
160
170
180
190
MOMENT/1000 INCH POUNDS
CENTRE OF GRAVITY ENVELOPE
50
55
PERFORMANCE & LOADING – 14
LOADING SYSTEM CHARLIE
CONFIGURATION: 4 SEATS
INSTRUCTIONS FOR USE OF LOADING SYSTEM
To check the loading of the aircraft before take-off, carry out a summation of weight and index units as
shown in the example below. Check the centre of gravity of the aircraft at Zero Fuel Weight and TakeOff Weight by use of the formula:
CG (mm aft of datum) = Index unit x 100
Weight
The CG must be within the envelope given at all times.
AIRCRAFT LIMITATIONS
Maximum take-off weight
Normal category:
Utility category:
Maximum baggage compartment baggage:
1115 KG
925 KG
122 KG
Notes:
1
2
3
Aircraft empty weight includes unusable fuel and undrainable oil
All arms are in mm aft of datum
1 index unit = 100 KG mm
_____________________________________________________
EXAMPLE:
Aircraft empty weight
Full oil
1 pilot + 1 passenger Row 1
2 passengers
Row 2
Baggage
Zero Fuel Weight
Fuel 140 litres
Take-off Weight
CG check
KG
687
7
140
160
20
1014
99
1113
IU
19,522
86
3,850
5,760
842
30,060
2,920
32,980
1.
At Zero Fuel Weight = (30,060 x 100) / 1014 = 2965 mm OK
2.
At Take-Off Weight = (32,980 x 100) / 1113 = 2963 mm OK
PERFORMANCE & LOADING – 15
LOADING SYSTEM CHARLIE
INDEX UNITS
Fuel
ARM: 2950
20
40
60
80
100
120
140
160
180
200
216
14
28
43
57
71
85
99
114
129
142
153
BAGGAGE
413
826
1,268
1,682
2,095
2,507
2,920
3,363
3,806
4,189
4,513
ARM: 4210
10
20
30
40
50
60
70
80
90
100
110
122
421
842
1,263
1,684
2,105
2,526
2,947
3,368
3,789
4,210
4,631
5,136
OCCUPANTS
KG
ROW 1
ROW 2
ARM: 2750 ARM: 3600
40
45
50
55
60
65
70
75
80
85
90
1,100
1,237
1,375
1,512
1,650
1,786
1,925
2,062
2,200
2,338
2,475
1,440
1,620
1,800
1,980
2,160
2,340
2,520
2,700
2,880
3,060
3,240
OIL ARM : 1230
US Quarts
LITRES
KG
INDEX UNITS
6
7
8
5.7
6.6
7.6
5.0
6.0
7.0
62
74
86
PERFORMANCE & LOADING – 16
LOADING SYSTEM CHARLIE
Figure 9
1200
1150
MAX AUW 1115 KG
1100
1050
950
AFT LIMIT 2896 mm
900
850
UTILITY CATEGORY
800
FWD LIMIT
KILOGRAMS
AFT LIMIT 3004 mm
NORMAL CATEGORY
1000
750
700
2680
2720
2760
2800
2840
2880
2920
2960
3000
CENTRE OF GRAVITY POSITION (mm AFT OF DATUM)
ALLOWABLE CENTRE OF GRAVITY ENVELOPE
CONVERSION FACTORS
1 inch = 25.4 mm
1 foot = 0.305 metre
1 lb = 0.454 KG
1 Imp gal = 1.201 US gal = 4.546 litres
100/130 aviation gasoline: Specific Gravity = 0.71
SCRIBBLE PAD – 17
PERFORMANCE & LOADING – 18
LOADING SYSTEM ECHO
CONFIGURATION: 6 SEATS
INSTRUCTIONS FOR USE OF LOADING SYSTEM
1
Moment Index chart (fig 10, page 20) may be used to determine the balance of the aeroplane.
Locate the weight (in KG) of a particular load item on the vertical scale and move horizontally to
the line representing the location of that item. From that point drop vertically to read off the
Moment Index for that item.
2
Obtain the aeroplane basic empty weight and index units from the examination question. Add up
the required total weight (Gross Weight) of the aeroplane and the corresponding Total Moment
Index.
3
Refer to the Centre of Gravity chart (fig 11, page 21). Locate the Gross Weight of the loaded
aeroplane (in KG) on the vertical scale and move horizontally to meet the vertical line
representing the Total Moment Index of the loaded aeroplane. If the point of intersection, which
represents the Centre of Gravity, falls in the shaded area, the aeroplane is correctly loaded.
Note: The Centre of Gravity must lie in the shaded area at ALL stages of flight.
Weight Limitations:
Balance Data:
Maximum Take-off Weight
Maximum Landing Weight
Maximum Zero Fuel Weight
2950 KG
2725 KG
2630 KG
The Mean Aerodynamic Chord (MAC) data is as follows:
Length of chord
1900 mm
Location of leading edge
2190 mm aft of datum
Centre of Gravity range is a follows:
2400 mm to 2680 mm at 2360 KG or less
2560 mm to 2680 mm at 2950 KG
Linear variation between the points given
Loading Data:
Location
Maximum Permissible Load
Seating:
Row 1 (Seats 1 & 2)
Pilot + 1 Passenger
Row 2 (Seats 3 & 4)
2 Passengers
Row 3 (Seats 5 & 7
2 Passengers
Cargo & Baggage Compts:
Forward Compt
55 KG
Left wing Compt.
55 KG
Right wing Compt.
55 KG
Rear Compartment
155 KG
Floor loading intensity
(All Compts) 450 KG/m2
Fuel:
Left main tank
50 gal
Right main tank
50 gal
Left auxiliary tank
40 gal
Right auxiliary tank
40 gal
Load Arm (mm Aft of Datum)
2290
3300
4300
500
3550
3550
5000
1780
1780
2800
2800
PERFORMANCE & LOADING – 19
LOADING SYSTEM ECHO (continued)
Note: All passenger seats weigh 5 KG each and may be removed to permit the carriage of additional
cargo or baggage in the cabin.
The maximum permissible load in the area otherwise occupied by a passenger seat is 82 KG.
If a passenger seat is removed, adjust the empty weight and empty moment.
EXAMPLE:
Aeroplane Basic Empty Weight
Row 1 (2 passengers)
Row 2 (2 passengers)
Row 3 (2 passengers)
Rear compartment
Zero Fuel Weight
Fuel in Main tanks
Take-off Weight
Fuel Burn-off
Landing Weight
WEIGHT
(KG)
1970
150
140
130
100
2490
200
2690
80
2610
MOMENT INDEX
(Refer to Figure 10)
478.0
34.0
46.3
56.0
50.0
664.3
35.5
699.8
14.3
685.5
Refer to the Centre of Gravity Chart (Fig 11, page 21) to assess whether the horizontal line from the
“Gross Weight” in question intersects the vertical line from its corresponding Total Moment Index in the
shaded area.
LOAD - KG
0
50
100
150
200
250
300
0
FWD COMP
10
20
30
40
50
PS
OM
C
NG
WI
ROW 1
(SEATS 1 AND 2)
MOMENT INDEX
MAINS FUEL
60
70
REAR COMP
ROW 3
(SEATS 5 AND 6)
ROW 2
(SEATS 3 AND 4)
AUX FUEL
80
PERFORMANCE & LOADING – 20
LOADING SYSTEM ECHO
Figure 10
GROSS WEIGHT - KG
2000
450
2100
2200
2300
2400
2500
2600
2700
2800
2900
3000
500
550
TOTAL MOMENT INDEX
600
650
CENTRE OF GRAVITY ENVELOPE
700
750
1 INDEX UNIT = 10,000 KG mm
PERFORMANCE & LOADING – 21
LOADING SYSTEM ECHO
Figure 11
PERFORMANCE & LOADING – 22
TAKE-OFF WEIGHT CHART
AIRCRAFT - ECHO Figure 12
0 10 20
DOWN
5
2950
2900
2800
2700
2600
2500
2400
2300
2200
2100
2000
2
3
4
5
6
4000
6000
10
40
8000
30
20
400
AIRFIELD PRESSURE
HEIGHT - FEET
SL
12000
2000
4000
START
HERE
6000
8000
10000
500
600
700
900
800
1000
1100
1400
1300
1200
TAKE-OFF DISTANCE
AVAILABLE - METRES
DENSITY HEIGHT - FEET
0
-10
2000
SHADE
TEMP
C
0
LONG WET GRASS
SHORT WET OR LONG DRY GRASS
REFERENCE LINE - SHORT DRY GRASS
10000
1
LEVEL 1
2
TAKE-OFF WEIGHT - KG
SURFACE
SLOPE PERCENT
TAIL
AMBIENT WIND
COMPONENT - KNOTS
TAKE-OFF SAFETY SPEED
KNOTS - IAS
98
96
94
92
HEAD
90
88
86
84
82
80
5 0 10 20
ZERO DEGREES
SEE SCALE
1.22
3200 RPM
37.4 IN Hg
UP
FLAP SETTING
TAKE-OFF SAFETY SPEED
DISTANCE FACTOR
POWER TO BE USED
RPM
MAN PRESS
AIRFIELD PRESSURE HEIGHT
FEET
0
12000
2000
4000
START
HERE
LANDING DISTANCE AVAILABLE
METRES
6000
10000
8000
30
6000
20
10
4000
0
DENSITY HEIGHT - FEET
40
2000
-10
SHADE
TEMP
C
500
0
2950
2900
2800
2700
2600
2500
2400
2300
2200
2100
2000
SLOPE PERCENT
8000
600
5
0
TAIL
10 20
UP
0 10 20
AMBIENT WIND
COMPONENT - KNOTS
5
HEAD
DOWN
80
82
84
86
88
90
92
94
45 DEGREES
SEE SCALE
1.26
10000
700
900
800
1000
2
FLAP SETTING
APPROACH SPEED
DISTANCE FACTOR
1100
1200
1300
1400
1500
1600
1
2
3
4
5
6
LEVEL 1
SLOPE PERCENT
PERFORMANCE & LOADING – 23
LANDING WEIGHT CHART
AIRCRAFT - ECHO
Figure 13
APPROACH SPEED
KNOTS - IAS
LANDING WEIGHT - KG
HELICOPTER – 24
A
AXIS OF
ROTATION
PLANE OF
ROTATION
Helicopter Figure “A”
A
AXIS OF
ROTATION
PLANE OF
ROTATION
Helicopter Figure “B”
HELICOPTER – 25
A
AXIS OF
ROTATION
PLANE OF
ROTATION
Helicopter Figure “C”
A
AXIS OF
ROTATION
PLANE OF
ROTATION
Helicopter Figure “D”
HELICOPTER – 26
LIFT
TOTAL
REACTION
TOTAL
REACTION
LIFT
DRAG
RELATIVE
AIRFLOW
DRAG
RELATIVE
AIRFLOW
Diagram 1
LIFT
TOTAL
REACTION
Diagram 2
TOTAL
REACTION
LIFT
DRAG
DRAG
RELATIVE
AIRFLOW
RELATIVE
AIRFLOW
Diagram 3
Diagram 4
Helicopter Figure “E”
POWER
Power available
we
Po
1
2
d
re
ui
q
e
rr
3
IAS (Kts)
Helicopter Figure “F”
4
NAVIGATION – 31
B
A
q nm
p nm
X
D 2 nm
D1 nm
Figure 16
A
B
p nm
q nm
X
D2 nm
D1 nm
Figure 17
B
q nm
X
p nm
A
D2 nm
D1 nm
Figure 18
NAVIGATION – 32
A
p nm
X
q nm
B
D2 nm
D1 nm
Figure 19
A
B
p nm
q nm
X
D2 nm
D1 nm
Figure 20
D2 nm
D1 nm
X
p nm
q nm
A
B
Figure 21
NAVIGATION – 33
A
p nm
X
q nm
B
D1 nm
D2 nm
Figure 22
A
B
p nm
q nm
X
D1 nm
D2 nm
Figure 23
D nm
TRACK = T M
A
p nm
B
Figure 24
NAVIGATION – 34
A
TRACK = T M
p nm
B
D nm
Figure 25
B
A
TRACK = T M
p nm
D nm
Figure 26
B
p nm
TRACK = T M
D nm
Figure 27
A
NAVIGATION – 35
m
50 n
30
20
nm
nm
LL4000
LL6000
LL8000
X
A
Figure 28
m
50 n
nm
35
nm
22
LL4000
LL6000
LL10000
X
A
Figure 29
H3
H3
H2
H2
H1
H1
CTR
R1
Class G
R2
R3
Figure 29A
NAVIGATION – 36
B
TMG
A
TRACK ERROR = E
REQUIRED TRACK
D nm
Figure 30
REQUIRED TRACK
A
TRACK ERROR = E
TMG
B
D nm
Figure 31
NAVIGATION – 37
A
B
C
D1 nm
D2 nm
Figure 32
X
A
B
P nm
Q nm
R nm
Figure 33
A
C
X
D1 nm
Figure 34
D2 nm
NAVIGATION – 38
B
A
p nm
D nm
Figure 35
B
A
p nm
X
D1 nm
D2 nm
Figure 36
B
A
p nm
D nm
Figure 37
NAVIGATION – 39
B
TMG
A
p nm
TRACK = T M
D nm
Figure 38
A
Prohibited Area Z
D2 nm
D1 nm
Figure 39
TOTAL DRAG
POWER REQUIRED
PRINCIPLES OF FLIGHT – 40
X
X Y
TAS
Figure 40
L
TAS
Figure 41
CL
D
X
ANGLE OF ATTACK
Figure 42
X
ANGLE OF ATTACK
Figure 43
SCRIBBLE PAD – 41
SCRIBBLE PAD – 42
SCRIBBLE PAD – 43
METEOROLOGY – MSL ANALYSIS CHARTS – 44
MSL ANALYSIS - Figure 48
10
YPDN
P
20
10
LOW
1012
YPPD
YBAS
B
R
YBTL
C
10 16
20
N
1020
HIGH
YBBN
M
30
J
YPPH
30
YPAD
YBHI
1016
40
YSSY
YMML
1008
40
YMHB
120
110
100
90
130
A
140
K
160
150
1 70
50
80
1000
992
50
MSL ANALYSIS - Figure 49
10
YPDN
10
P
1012
20
YBTL
YPPD
J
20
R
YBAS
C
1020
YBBN
30
1036
30
YPPH
101
2
100
4
40
98
100
80
YSSY
YMML
988
A
90
M
996
40
0
110
B
1012
102
0
HIGH
1028
YPAD
YBHI
1020
120
130
YMHB
140
LOW
K
50
150
160
50
N
MSL ANALYSIS - Figure 49
1 70
METEOROLOGY – ARFOR – 45
ARFOR No. 1
AREA 21 (21)
AMEND AREA FORECAST 090200 TO 091700 AREA 21
OVERVIEW
SURFACE TROUGH AT 2200 Z: THROUGH YYNG/YMER
0500 Z: YBTH/YSNW
1100 Z : EAST OF AREA
SCATTERED SHOWERS AND THUNDERSTORMS. INCLUDING ISOLATED HAIL. AREAS OF
RAIN. CONTRACTING EASTWARDS ISOLATED FOG AFTER 1100Z
REFER SIGMET RE SQUALLS AND HAIL.
SUBDIVISIONS:
A:
E OF TROUGH :
B:
W OF TROUGH
AMD WIND
2000
5000
7000
10000
14000
18500
A : 350/25
340/30
340/35
340/40
340/50 MS04
340/55 MS14
B : 260/25
260/30
260/30
280/30 ZERO
280/40 MS08
280/60 MS17
AMD CLOUD
AREAS OF BKN ST 1000/3000 W SLOPES 3000/5000 RANGES.
ALSO WITH PRECIPITATION 1000/3000 COAST/SEA
BKN CUSC 2500/10000 W SLOPES 4500/11000 W RANGES
SCT CUSC 2500/10000 COAST/SEA 4500/11000 E RANGES
ISOL CB 5000/35000
BKN ACAS ABV 10000 CONTRACTING E
AMD WEATHER
RA CONTRACTING E SH/TS WITH HAIL FOG AFTER 11
VISIBILITY
5000M SH/RA 3000 TS
AMD FREEZING LEVEL
A: 12000
B: 9500
AMD ICING
MOD IN CU 9500/11000 AND AC
AMD TURBULENCE
MOD WITH CU AND AC
MOD TO ISOL SEV RANGES/COAST/6ONM OFFSHORE
NOTE: REFER SIGMET RE SQUALLS AND HAIL
METEOROLOGY – ARFOR – 46
ARFOR No. 2
AREA 21 (21)
AMEND AREA FORECAST 090100 TO 091700 AREA 21
OVERVIEW:
SURFACE TROUGH AT 0400 Z : THROUGH YSWG/YMCO
1000 Z : YCWR/YMRY
1600 Z : EAST OF AREA
SCATTERED SHOWERS AND THUNDERSTORMS. INCLUDING ISOLATED HAIL. AREAS OF
RAIN. CONTRACTING EASTWARDS ISOLATED FOG AFTER 1600Z REFER SIGMET RE
SQUALLS AND HAIL.
SUBDIVISIONS:
A:
E OF TROUGH
B:
W OF TROUGH
AMD WIND:
2000
5000
7000
10000
14000
18500
A:
350/25
340/30
340/35
340/40
340/50 MS04
340/55 MS14
B:
260/25
260/30
260/30
280/30 ZERO
280/40 MS08
280/60 MS17
AMD CLOUD:
AREAS OF SCT ST 1000/3000 W SLOPES 3000/5000 RANGES.
ALSO WITH PRECIPITATION 1000/3000 COAST/SEA
BKN CUSC 2500/10000 W SLOPES 4500/11000 W RANGES
SCT CUSC 2500/10000 COAST/SEA 4500/11000 E RANGES
ISOL CB 5000/35000
BKN ACAS ABV 10000 CONTRACTING E
AMD WEATHER:
RA CONTRACTING E SH/TS WITH HAIL FOG AFTER 16
VISIBILITY
5000M SH/RA 3000 TS
AMD FREEZING LEVEL
A: 12000
B: 9500
AMD ICING
MOD IN CU 9500/11000 AND AC
AMD TURBULENCE:
MOD WITH CU AND AC
MOD TO ISOL SEV RANGES/COAST/6ONM OFFSHORE
METEOROLOGY – ARFOR – 47
ARFOR No. 3
AREA 21 (21)
AMEND AREA FORECAST 092300 TO 101100 AREA 21
OVERVIEW:
WEAK SURFACE TROUGH THROUGH NSW SLOPING WEST WITH HEIGHT,
AT 23 Z:
10000FT ABOUT PARKES/MORUYA
18500FT ABOUT WAGGA/ORBOST
SUBDIVISIONS:
A:
E OF TROUGH
B:
W OF TROUGH
AMD WIND:
2000
5000
7000
10000
14000
A: 240/25
250/25
250/25
280/35 MS04
280/50 MS11
B: 240/30
240/30
240/30
240/30 MS06
240/35 MS13
AMD CLOUD
SCT ST 1000/3000 SW SLOPES. BKN RANGES TILL 02
SCT CUSC 5000/7000 RANGES/SLOPES. BKN SLOPES IN S
SCT CU 4000/7000 SEA/COAST
AMD WEATHER
ISOL SHOWERS RANGES/W SLOPES S OF 35S
ISOL SHOWER SEA
VISIBILITY:
5000M SHOWERS
AMD FREEZING LEVEL:
6000 S OF 35S / 9000 N
AMD ICING
MOD IN CU TOPS
AMD TURBULENCE
MOD BLW 10000 RANGES/E
18500
280/70 MS20
220/45 MS22
METEOROLOGY – ARFOR – 48
ARFOR No. 4
AREA 21 (21)
AMEND AREA FORECAST 092300 TO 101100 AREA 21
OVERVIEW:
WEAK SURFACE TROUGH AT 0200 Z : THROUGH YSWG/YORB
0700 Z : YPKS/YMRY
1100 Z : YBTH/YSNW
SUBDIVISIONS:
A:
E OF TROUGH
B:
W OF TROUGH
AMD WIND :
2000
5000
7000
10000
A: 240/25
250/25
250/25
280/35 MS04
B: 240/30
240/30
240/30
240/30 MS06
AMD CLOUD:
SCT ST 1000/3000 SW SLOPES. BKN RANGES TILL 08
SCT CUSC 5000/7000 RANGES/SLOPES. BKN SLOPES IN S
SCT CU 4000/7000 SEA/COAST
AMD WEATHER:
ISOL SHOWERS RANGES/W SLOPES S OF 35S
ISOL SHOWER SEA
VISIILITY:
5000M SHOWERS
AMD FREEZING LEVEL:
A: 8000
B: 9000
AMD ICING
MOD IN CU TOPS
AMD TURBULENCE:
MOD BLW 10000 RANGES/E
14000
280/50 MS11
240/35 MS13
18500
280/70 MS20
220/45 MS22
METEOROLOGY – ARFOR – 49
ARFOR No. 5
AREA 21 (21)
AREA FORECAST 062100 TO 071100 AREA 21
OVERVIEW:
ISOLATED SHOWERS CHIEFLY ALONG COAST WITH AREAS OF LOW CLOUD TILL 04Z
PATCHY RAIN NORTH OF ORANGE/SYDNEY. ISOL FOGS RANGES/EAST TILL 23Z
SUBDIVISIONS:
NIL
WIND
2000
5000
7000
10000
14000
VRB/15
260/15
260/15
260/25 ZERO
270/30 MS08
CLOUD
AREAS OF BKN ST 1000/3000 SEA/COAST TILL04
3000/5000 RANGES IN E TILL 02
AREAS OF CU/SC 3000/8000 SEA/COAST ISOL TOPS SEA 20000
SCT CU/SC 4000/8000 RANGES, BKN IN S AND E
SCT SC 5000/8000 W SLOPES
AREAS OF BKN ACAS ABOVE 11000
WEATHER:
SH IN E. PATCHY RA N OF YORG/YSSY
ISOL FOG RANGES AND EAST TILL 23
VISIBILITY:
5000 SH/RA
FREEZING LEVEL
10000
ICING
MOD IN CU/AC
TURBULENCE:
MOD IN CU/AC
CRITICAL LOCATIONS: (HEIGHT ABOVE MSL)
MT VICTORIA:
BKN SC 4000
FM23 5000M SH BKN CU 5000
BOWRAL:
500M FOG
FM22 5000M BKN ST 3000
FM00 8000M BKN SC 4500
18500
270/40 MS17
METEOROLOGY – ARFOR – 50
ARFOR No. 6
AREA 22 (22)
AREA FORECAST 112300 TO 121100 AREA 22
OVERVIEW:
THUNDERSTORMS WITH HAIL (SMALL) DEVELOPING IN W AREA 22 EXTENDING E
SCATTERED SHOWERS/DRIZZLE
WIDESPREAD LOW CLOUD, BECOMING SCATTERED NW
ISOLATED SEVERE TURBULENCE BELOW 8000
REFER SIGMET FOR LATEST DETAILS OF SEVERE ICING
WIND:
2000
5000
7000
10000
14000
270/40
270/35
260/40
270/45 MS10
270/50 MS18
CLOUD:
OCNL CB 2500/28000 W AREA 22 EXTENDING E
BKN ST 800/3000, BECOMING SCT NW
BKN CU 2500/15000
WEATHER:
TS (HAIL) SH/DZ
VISIBILITY:
4000M SH/DZ/TS
FREEZING LEVEL:
4000S/5000N
ICING:
REFER SIGMET
TURBULENCE:
ISOL SEV BELOW 8000
18500
260/60 MS28
SCRIBBLE PAD – 51
SCRIBBLE PAD – 52
SCRIBBLE PAD – 53
METEOROLOGY – ARFOR BOUNDARIES – 54
SCRIBBLE PAD – 55
SCRIBBLE PAD – 56