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Australian GovernmentCivil 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 CONTENT PAGE
Company Policy 3 Figs 16 / 17 / 18: Navigation 31 Figs 1 / 2 : Aerodrome Markers/Markings 4 Figs 19 / 20 / 21: Navigation 32 Scribble pad 5 Figs 22 / 23 / 24: Navigation 33 Fig 3 - Take-off Weight Chart 6 Figs 25 / 26 / 27: Navigation 34 Fig 4 - Landing Distance Chart 7 Figs 28 / 29 / 29A: Navigation 35 Fig 5 - Take-off Weight Chart 8 Figs 30 / 31: Navigation 36 Fig 6 - Landing Chart 9 Figs 32 / 33 / 34: Navigation 37 Loading System Alpha: Instructions 10 Figs 35 / 36 / 37: Navigation 38 Fig 7 - Loading System Alpha 11 Figs 38 / 39: Navigation 39 Loading System Bravo: Instructions 12 Figs 40 / 41 / 42 / 43: Principles of Flight 40 Fig 8 - Loading System Bravo 13 Scribble pad 41 Loading System Charlie: Instructions 14 Scribble pad 42 Loading System Charlie: Index Units 15 Scribble pad 43 Fig 9 - Loading System Charlie 16 Figs 48 / 49 Meteorology
MSL Analysis charts 44
Scribble pad 17 Loading System Echo: Instructions 18 Meteorology – ARFOR No. 1 45 Loading System Echo: Instructions (Continued)
19 Meteorology – ARFOR No. 2 46 Meteorology – ARFOR No. 3 47
Fig 10 - Loading System Echo: Index Units 20 Meteorology – ARFOR No. 4 48 Fig 11 - Loading System Echo: CG Envelope
21 Meteorology – ARFOR No. 5 49 Meteorology – ARFOR No. 6 50
Fig 12 - Take-off Weight Chart: Aircraft Echo
22 Scribble pad 51 Scribble pad 52
Fig 13 - Landing Weight Chart: Aircraft Echo
23 Scribble pad 53 Meteorology - PCA ARFOR Boundaries for Flights
54 Helicopter Figures “A” and “B” 24 Helicopter Figures “C” and “D” 25 Scribble pad 55 Helicopter Figures “E” and “F” 26 Scribble pad 56 WAC Extract: (3219) TOWNSVILLE 27 WAC Extract: (3456) SYDNEY 28 & 29 WAC Extract: (3356) BOURKE 30 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
AERODROMEMARKERS
Figure 1
AERODROMEMARKINGS
Figure 2
(i)
(ii)
(iii)
(iv)
(i)
(ii)
(iii)
(iv)
PERFORMANCE & LOADING – 6
AIRF
IELD
PRE
SSU
RE H
EIG
HT
- FT
TAKE
-OFF
DIS
TAN
CE A
VAIL
ABLE
- M
ETRE
S
SHADETEMP
CSL
2000
4000
6000
8000
400
STARTHERE
-10010203040
500600700800
900
1000
1100
1200
130014001500
LONG WET GRASS SURFACELONG DRY OR SHORT WET GRASS SURFACEREFERENCE LINE SHORT DRY GRASS SURFACE
DOWN
UP
SLOPE PERCENT
2LEVEL
2
4
HEAD
TAIL
1050
1100
1000
950
900
850
AMBIENT WIND COMPONENT - KNOTS
(A)
(B)
5
TAKE-OFF WEIGHT CHARTFigure 3
1090 KG
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 USEDFLAP SETTINGTAKE-OFF SAFETY SPEEDTAKE-OFF DISTANCE FACTOR
FULL THROTTLE10 DEGREES60 KIAS1.15
0 10 20
TAKE
-OFF
WEI
GH
T -
KG
PERFORMANCE & LOADING – 7
SHAD
E TE
MPE
RATU
RE C
5040
3020
010
-10
SLO
PE P
ERCE
NT
64
02
2
AMBI
ENT
WIN
DCO
MPO
NEN
T -
KT200
105
200
300
400
500
600
700
800
900
1000
LANDING DISTANCE CHARTFigure 4
AIRF
IELD
PRE
SSU
REH
EIG
HT
- FE
ET
CLIMB LIMIT WEIGHT - KG
1000
6000
5000
4000
1050
1055
MAX
NO
TE:
L
AND
ING
WEI
GH
T M
UST
N
OT
EXCE
ED C
LIM
B
WEI
GH
T LI
MIT
BEL
OW
FLAP
SET
TIN
G
4
0 D
EGRE
ESAP
PRO
ACH
SPE
ED
65
KT IA
SLA
ND
ING
DIS
TAN
CE F
ACTO
R 1
.15 NOTE:
LANDING DISTANCE REQUIRED IS INDEPENDENT OF LANDING WEIGHT.
6000
REFERENCE LINE
REFERENCE LINE
LANDING DISTANCE REQUIRED - METRES
4000
2000
S.L.
PERFORMANCE & LOADING – 8
SHAD
E TE
MPE
RATU
RE C
4030
200
10-1
0
SLO
PE P
ERCE
NT
64
02
2
AMBI
ENT
WIN
DCO
MPO
NEN
T -
KT
200
105
NO
TE:
TA
KEO
FF W
EIG
HT
MU
ST N
OT
EXCE
ED
CLIM
B W
EIG
HT
LIM
IT B
ELO
W
FLAP
SET
TIN
GTA
KEO
FF S
AFET
Y SP
EED
POW
ER S
ETTI
NG
RPM
CHAR
T DI
STAN
CE F
ACTO
R
SURF
ACE
TAKE
-OFF
WEI
GH
T -
KG
1000
1200
1600
1800
1400
2000
2200
2400 200
400
600
800
TAKE-OFF DISTANCE AVAILABLE - METRESTA
KE
-OFF
WE
IGH
T C
HA
RT
Figu
re 5
850
900
950
1000
1055
CLIMB LIMIT WEIGHT - KG
AIRF
IELD
PRE
SSU
RE H
EIG
HT
- FE
ET
60005000
4000
REFERENCE LINE
REFERENCE LINE
6000
REFERENCE LINE HARD SEALED SURFACESHORT DRY GRASSSHORT WET OR LONG DRY GRASS
LONG WET GRASS
1055
750
TAKE
-OFF
WEI
GH
T -
KG
800
850
900
950
1000
10501055
750
800
850
900
950
1000
1050
ZERO
64
KT IA
SFU
LL T
HRO
TTLE
NO
T LE
SS T
HAN
235
01.
15 4000 20
00
0
PERFORMANCE & LOADING – 9
LANDING CHARTFigure 6
AIRF
IELD
PRE
SSU
RE H
EIG
HT
- FT
LAN
DIN
G D
ISTA
NCE
REQ
UIR
ED -
MET
RES
SHADETEMP
CSL
2000
4000
6000
8000
400
-10010203040
450 5
500
550
600
650
DOWN
UP
SLOPE PERCENT2LEVEL
4
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 SETTINGAPPROACH SPEEDLANDING DISTANCE FACTOR
30 DEGREES58 KIAS1.15
(A)
1080KG
AMBIENT WIND COMPONENT - KNOTS
20100TAIL HEAD
2000
4000
6000
8000
CLIMB WEIGHT LIMIT
2
800 900 1000 1100
AIRF
IELD
PRE
SSU
RE H
EIG
HT
- FT
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 right- hand 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 1050 KG Empty Index units -260 Row 1 150 KG (2 persons) Row 2 (forward facing) 160 KG (2 persons) Row 3 120 KG (2 persons) Nose baggage 40 KG ----------------- Zero Fuel Wt = 1520 KG Rear baggage Nil Fuel 113 KG ---------------- Take-Off Wt = 1633 KG Note: Basic Empty Weight includes unusable fuel and full oil.
PERFORMANCE & LOADING – 11
LOADING SYSTEM ALPHA
Figure 7
AIRCRAFT BASIC INDEX UNITS+200+1000-100-200-300-400
50 KG/DIV
77 KG/DIV
50 KG/DIV
77 KG/DIV
50 KG/DIV
77 KG/DIV
50 KG/DIV
77 KG/DIV
10 KG/DIV
10 KG/DIV
WEIGHT (KG)
ROW 1OCCS
ROW 2OCCS
ROW 2OCCS
ROW 3OCCS
NOSEBAGGAGE
REARBAGGAGE
FUEL
(FORWARD FACING)
(AFT FACING)
(45 KG MAXIMUM)
(MAXIMUM 356 LITRES 252 KG)
(45 KG MAXIMUM)
NIL SCALE
ZERO FUEL WEIGHT
TAKEOFF WEIGHT
GROSS WEIGHT (KG)
1633 KG1600 KG
1500 KG
1400 KG
1300 KG
1200 KG
1100 KG
1633 KGMAXIMUM TAKE-OFF WEIGHT
EXAMPLE
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: 1000 KG / 2200 lbs Utility category: 841 KG / 1850 lbs Maximum baggage compartment baggage: 53 KG / 120 lbs Notes:
1 The aircraft is fitted with standard tanks (37 US Gallons at 6 lbs / gallon) 2 Empty weight includes unusable fuel and undrainable oil 3 Obtain Moment / 1000 inch pounds from the loading graph
_____________________________________________________ EXAMPLE:
WEIGHT (LBS) ARM (IN) MOMENT/1000 IN LB Empty weight 1260 80 100.80 Oil 15 32 .48 Fuel (141 litres) 222 91 20.02 Pilot & Co-Pilot 320 91 29.12 Rear seat passengers 350 126 44.10 Baggage 25 151 3.78 Take-Off Weight 2192 198.30
Check CG is within the envelope
PERFORMANCE & LOADING – 13
LOADING SYSTEM BRAVO
Figure 8Add weight of items to be carried to aeroplane licensedempty weight. Add moment/1000 of items to be carriedto total aeroplane moment/1000. Use Centre of GravityEnvelope to determine acceptibility.
0 5 10 15 20 25 30 35 40 45 50 550
100
200
300
400
500
LOAD
- W
EIG
HT
IN P
OU
ND
S
MOMENT/1000 INCH POUNDS
120 130 140 150 160 170 180 190 200 2101400
1500
1600
1700
1800
1900
2000
2100
2200
LOAD
ED A
IRC
RAFT
WEI
GH
T I N
PO
UN
DS
MOMENT/1000 INCH POUNDS
NORM
AL C
ATEG
ORY
UTILIT
Y CA
TEGO
RY
CENTRE OF GRAVITY ENVELOPE
PILOT AND COPILOT
STD FUEL (37 gal. useable - 6 lbs/gal.)
OPT FUEL (51 gal. useable - 6 lbs/gal.)
LOADING GRAPH
BAGGAGE
CARGO
REAR SEAT PASSENGERS
LOADING GRAPH
CENTRE OF GRAVITY ENVELOPE
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 Take-Off 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: 1115 KG Utility category: 925 KG Maximum baggage compartment baggage: 122 KG Notes:
1 Aircraft empty weight includes unusable fuel and undrainable oil 2 All arms are in mm aft of datum 3 1 index unit = 100 KG mm
_____________________________________________________
EXAMPLE:
KG IU Aircraft empty weight 687 19,522 Full oil 7 86 1 pilot + 1 passenger Row 1 140 3,850 2 passengers Row 2 160 5,760 Baggage 20 842
Zero Fuel Weight 1014 30,060 Fuel 140 litres 99 2,920
Take-off Weight 1113 32,980 CG check 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 BAGGAGE ARM: 4210 20 14 413 10 421 40 28 826 20 842 60 43 1,268 30 1,263 80 57 1,682 40 1,684 100 71 2,095 50 2,105 120 85 2,507 60 2,526 140 99 2,920 70 2,947 160 114 3,363 80 3,368 180 129 3,806 90 3,789 200 142 4,189 100 4,210 216 153 4,513 110 4,631
122 5,136
OCCUPANTS
KG ROW 1 ARM: 2750
ROW 2 ARM: 3600
40 1,100 1,440 45 1,237 1,620 50 1,375 1,800 55 1,512 1,980 60 1,650 2,160 65 1,786 2,340 70 1,925 2,520 75 2,062 2,700 80 2,200 2,880 85 2,338 3,060 90 2,475 3,240
OIL ARM : 1230
US Quarts LITRES KG INDEX UNITS 6 5.7 5.0 62 7 6.6 6.0 74 8 7.6 7.0 86
PERFORMANCE & LOADING – 16
LOADING SYSTEM CHARLIEFigure 9
2680 2720 2760 2800 2840 2880 2920 2960 3000
750
800
850
900
950
700
1000
1050
1100
1150
1200
KILO
GRA
MS
CENTRE OF GRAVITY POSITION (mm AFT OF DATUM)
FWD L
IMIT
MAX AUW 1115 KG
NORMAL CATEGORY
UTILITY CATEGORY
AFT
LIM
IT 2
896
mm
AFT
LIM
IT 3
004
mm
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
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: Maximum Take-off Weight 2950 KG Maximum Landing Weight 2725 KG Maximum Zero Fuel Weight 2630 KG Balance Data: 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 Load Arm (mm Aft of Datum) Seating: Row 1 (Seats 1 & 2) Pilot + 1 Passenger 2290 Row 2 (Seats 3 & 4) 2 Passengers 3300 Row 3 (Seats 5 & 7 2 Passengers 4300 Cargo & Baggage Compts: Forward Compt 55 KG 500 Left wing Compt. 55 KG 3550 Right wing Compt. 55 KG 3550 Rear Compartment 155 KG 5000 Floor loading intensity (All Compts) 450 KG/m2
Fuel: Left main tank 50 gal 1780 Right main tank 50 gal 1780 Left auxiliary tank 40 gal 2800 Right auxiliary tank 40 gal 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:
WEIGHT (KG)
MOMENT INDEX (Refer to Figure 10)
Aeroplane Basic Empty Weight 1970 478.0 Row 1 (2 passengers) 150 34.0 Row 2 (2 passengers) 140 46.3 Row 3 (2 passengers) 130 56.0 Rear compartment 100 50.0
Zero Fuel Weight 2490 664.3 Fuel in Main tanks 200 35.5
Take-off Weight 2690 699.8 Fuel Burn-off 80 14.3
Landing Weight 2610 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.
PERFORMANCE & LOADING – 20
LOADING SYSTEM ECHOFigure 10
010
2030
4050
6070
80050100
150
200
250
LOAD - KG
MO
MEN
T IN
DEX
ROW
3(S
EATS
5 A
ND
6)
300
MAI
NS
FUEL
AUX
FUEL
WIN
G C
OMPS
FWD
CO
MP
REAR
CO
MP
ROW
1(S
EATS
1 A
ND
2)
ROW
2(S
EATS
3 A
ND
4)
PERFORMANCE & LOADING – 21
LOADING SYSTEM ECHOFigure 11
450
500
550
600
650
7 00
7 50
2000
2100
2200
2300
2400
2500
2600
2700
2800
GROSS WEIGHT - KG
TOTA
L M
OM
ENT
IND
EX
2900
3000
1 IN
DEX
UN
IT =
10,
000
KG m
m1
IND
EX U
NIT
= 1
0,00
0 KG
mm
CEN
TR
E O
F G
RAV
ITY
EN
VE
LOPE
PERFORMANCE & LOADING – 22
AIRFIELD PRESSUREHEIGHT - FEET
TAKE-OFF DISTANCEAVAILABLE - METRES
SL
2000
4000
6000
8000
STAR
TH
ERE
SLO
PE P
ERCE
NT
AMBI
ENT
WIN
DCO
MPO
NEN
T -
KNO
TS
TAKE-OFF WEIGHT CHARTAIRCRAFT - ECHO Figure 12
LEVE
LFLAP SETTINGTAKE-OFF SAFETY SPEEDDISTANCE FACTORPOWER TO BE USED RPM MAN PRESS
ZERO DEGREESSEE SCALE1.223200 RPM37.4 IN Hg
TAKE-OFF WEIGHT - KG
1000
0
DEN
SITY
HEI
GH
T -
FEET
020
0040
0080
0060
0010
000
8000
2500
2400
2300
2000
2100
2200
2600
2700
2800
2900
2950
SURF
ACE
TAKE-OFF SAFETY SPEEDKNOTS - IAS
90 88 86 80828492949698
1200
0
600
700
800
900
1000
1100
1200
1300
1400
500
400
UP
DOW
N
HEA
D
TAIL
2010
05
12
1 2 3 4 5 6
2010
05
SHAD
ETE
MP
C40
3020
100
-10
LONG WET GRASSSHORT WET OR LONG DRY GRASSREFERENCE LINE - SHORT DRY GRASS
PERFORMANCE & LOADING – 23
LANDING WEIGHT CHARTAIRCRAFT - ECHO
Figure 13
AIRFIELD PRESSURE HEIGHTFEET
LANDING DISTANCE AVAILABLEMETRES
0
2000
4000
6000
8000
STAR
TH
ERE
SLO
PE P
ERCE
NT
AMBI
ENT
WIN
DCO
MPO
NEN
T -
KNO
TS
LEVE
L
FLAP SETTINGAPPROACH SPEEDDISTANCE FACTOR
45 DEGREESSEE SCALE1.26
LANDING WEIGHT - KG
1000
0
DEN
SITY
HEI
GH
T -
FEET
020
0040
0080
0060
0010
000
8000
2500
2400
2300
2000
2100
2200
2600
2700
2800
2900
2950
APPROACH SPEEDKNOTS - IAS
90 88 86 80828492
1200
0
1500 700
800
900
1000
1100
1200
1300
1400
600
500
UP
DO
WN
HEA
D
TAIL
2010
05
12
1 2 3 4 5 6
2010
05
SHAD
ETE
MP
C40
3020
100
-10
1600
94
SLOPE PERCENT
HELICOPTER – 24
Helicopter Figure “A”
AXIS
OF
R OTA
TIO
N
A
PLANE OFROTATION
Helicopter Figure “B”
AXI S
OF
ROT A
T IO
N
A
PLANE OFROTATION
HELICOPTER – 25
AXIS
OF
ROTA
TIO
N
PLANE OFROTATION
A
Helicopter Figure “C”
Helicopter Figure “D”
PLANE OFROTATION
AXIS
OF
ROTA
TIO
N
A
HELICOPTER – 26
Helicopter Figure “E”
RELATIVEAIRFLOW
LIFTTOTAL
REACTION
DRAG
RELATIVEAIRFLOW
DRAG
RELATIVEAIRFLOW
LIFTTOTAL
REACTION
DRAG
RELATIVEAIRFLOW
LIFTTOTAL
REACTION
DRAG
Diagram 1 Diagram 2
Diagram 3 Diagram 4
LIFTTOTAL
REACTION
Helicopter Figure “F”
POW
ER
IAS (Kts)
Power available
Power r
equir
ed
1 2 3 4
NAVIGATION – 31
Figure 16
D nm
AB
p nmq nm
D nm1 2
X
Figure 17
Figure 18
D nm
BA
q nmp nm
D nm1 2
D nm
B
A
q nm
p nm
D nm1 2
X
X
NAVIGATION – 32
Figure 19
D nm D nm1 2
A
p nm
B
q nmX
Figure 20
Figure 21
BA
q nmp nm
D nm D nm1 2
D nm D nm1 2
A
p nm
B
q nm
X
X
NAVIGATION – 33
Figure 22
D nm
Figure 23
D nm1 2
B
A
q nm
p nm
B
q nm
D nm D nm1 2
A
p nm
X
X
Figure 24
D nm
TRACK = T M
A
B
p nm
NAVIGATION – 34
Figure 25
D nm
Figure 26
B
p nm
A
A
D nm
p nm
B
TRACK = T M
TRACK = T M
Figure 27
B
p nmA
D nm
TRACK = T M
NAVIGATION – 35
Figure 28
Figure 29
A
LL4000 LL6000 LL8000
20 nm
30 nm
50 nm
X
A
LL4000 LL6000 LL10000
22 nm
35 nm
50 nm
X
Figure 29A
R1R2
R3
H1
H2
H3
CTR Class G
H3
H2
H1
NAVIGATION – 36
Figure 30
D nm
B
AREQUIRED TRACK
TMG
TRACK ERROR = E
Figure 31
D nm
B
A
REQUIRED TRACK
TMG
TRACK ERROR = E
NAVIGATION – 37
Figure 32
D nm D nm1 2
A B C
P nm
Figure 33
A B
Q nm R nm
X
Figure 34
D nm D nm1 2
A CX
PRINCIPLES OF FLIGHT – 40
Figure 40
TOTA
L D
RAG
TAS
Figure 41PO
WER
REQ
UIR
E D
TASX X Y
Figure 42
L
ANGLE OF ATTACK
Figure 43
C
X X
ANGLE OF ATTACK
LD
METEOROLOGY – MSL ANALYSIS CHARTS – 44
10
20
30
10
20
30
160150
140
100
90
YBTL
YBBN
YSSY
YMML
YMHB
YPAD
YPPH
YPPD
YPDN
YBAS
HIGH
LOW
A
C
B
1020
1016
1008
1000
992
R
P
M
N
130
17050
110
80
4040
50
K
10161012
120
YBHI
MSL ANALYSIS - Figure 48
J
80
100110
150
120
50
130 140
10
20
30
10
20
30
4040
YPDN
YBTL
YBBN
YMHB
YMML
YPAD
YPPH
YPPD
YBAS
LOW
B
N
M
50
A
HIGH
K
J
R
P
10201020
1012
1012
YSSY
1036
1028
1020
1012
1004
996
988
980
160170
YBHI
MSL ANALYSIS - Figure 49
MSL ANALYSIS - Figure 49
C
90
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 18500
A: 240/25 250/25 250/25 280/35 MS04 280/50 MS11 280/70 MS20
B: 240/30 240/30 240/30 240/30 MS06 240/35 MS13 220/45 MS22
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
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 14000 18500
A: 240/25 250/25 250/25 280/35 MS04 280/50 MS11 280/70 MS20
B: 240/30 240/30 240/30 240/30 MS06 240/35 MS13 220/45 MS22
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
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 18500
VRB/15 260/15 260/15 260/25 ZERO 270/30 MS08 270/40 MS17
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
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 18500
270/40 270/35 260/40 270/45 MS10 270/50 MS18 260/60 MS28
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