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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)

SCRIBBLE PAD – 5

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


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.


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


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


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.


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


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


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


LOADING SYSTEM CHARLIE CONFIGURATION: 4 SEATS


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


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


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

SCRIBBLE PAD – 17


LOADING SYSTEM ECHO CONFIGURATION: 6 SEATS


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


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.


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)


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


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


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

NAVIGATION – 38

Figure 37

D nm

A

B

p nm

Figure 35

D nm

A

B

Figure 36

p nm

AX

B

p nm

D nm D nm1 2

NAVIGATION – 39

Figure 38

D nm

B

A

TMG

TRACK = T M

p nm

A Prohibited Area Z

D nm D nm1 2

Figure 39

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

SCRIBBLE PAD – 41

SCRIBBLE PAD – 42

SCRIBBLE PAD – 43

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



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




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




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




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



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



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

SCRIBBLE PAD – 51

SCRIBBLE PAD – 52

SCRIBBLE PAD – 53

METEOROLOGY – ARFOR BOUNDARIES – 54

SCRIBBLE PAD – 55

SCRIBBLE PAD – 56

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