annexes 033-cqb release 10

JAAAppendices

Technical Realization: LPLUS 2002

JAA Appendices, Subject: 010 Page Edition:12-2002 1

Table Of Contents033-3301 A 10033-3302 A 11033-3305 A 12033-3306 A 13033-3307 A 14033-3308 A 15033-3309 A 16033-3311 A 17033-3312 A (separate issued paper - hard copy only)033-3313 A (separate issued paper - hard copy only)033-3314 A (separate issued paper - hard copy only)033-3315 A (separate issued paper - hard copy only)033-3316 A (separate issued paper - hard copy only)033-3317 A (separate issued paper - hard copy only)033-3318 A 18033-3320 A 19033-3320 B 20033-3320 C 21033-3321 A 22033-3322 A 23033-3323 A 24033-3324 A 25033-3327 A 26033-3906 A 27033-3907 A 28033-3908 A (separate issued paper - hard copy only)033-3909 A (separate issued paper - hard copy only)033-3910 A 29033-3911 A (separate issued paper - hard copy only)033-3911 B 30033-3912 A (separate issued paper - hard copy only)033-3912 B 31033-4616 A 32033-4622 A 33033-4623 A 34033-4735 A 35033-4736 A 36033-4737 A 37033-4738 A 38033-9543 A 39033-9546 A 40033-9550 A 41033-9551 A 42033-9552 A 43033-9553 A 44

033-9554 A 45033-9554 B 46033-9556 A 47033-9557 A 48033-9558 A 49033-9562 A 50033-9564 A 51033-9571 A 52033-9572 A 53033-9573 A 54033-9574 A 55033-9575 A 56033-9576 A (separate issued paper - hard copy only)033-9578 A 57033-9579 A 58033-9579 B 59033-9579 C 60033-9579 D 61033-9691 A 62033-9694 A 63033-9694 B 64033-9695 A 65033-9696 A 66033-9697 A 67033-9698 A 68033-9699 A 69033-9699 B 70033-9700 A 71033-9701 A 72033-9702 A 73033-9703 A 74033-9704 A 75033-9705 A 76033-9706 A 77033-9707 A (separate issued paper - hard copy only)033-9707 B 78033-9708 A 79033-9709 A 80033-9710 A (separate issued paper - hard copy only)033-9710 B 81033-9710 C 82033-9712 A 83033-9712 B 84033-9715 A 85033-9716 A 86033-9719 A (separate issued paper - hard copy only)

033-9721 A (separate issued paper - hard copy only)033-9722 A (separate issued paper - hard copy only)033-9723 A (separate issued paper - hard copy only)033-9724 A (separate issued paper - hard copy only)033-9726 A (separate issued paper - hard copy only)033-9727 A (separate issued paper - hard copy only)033-9728 A (separate issued paper - hard copy only)033-9729 A (separate issued paper - hard copy only)033-9730 A (separate issued paper - hard copy only)033-9732 A 87033-9733 A 88033-9734 A (separate issued paper - hard copy only)033-9735 A (separate issued paper - hard copy only)033-9736 A (separate issued paper - hard copy only)033-9737 A (separate issued paper - hard copy only)033-9738 A (separate issued paper - hard copy only)033-9739 A (separate issued paper - hard copy only)033-10989 A (separate issued paper - hard copy only)033-10990 A (separate issued paper - hard copy only)033-10991 A (separate issued paper - hard copy only)033-10992 A (separate issued paper - hard copy only)033-10993 A (separate issued paper - hard copy only)033-10994 A (separate issued paper - hard copy only)033-10995 A (separate issued paper - hard copy only)033-10996 A (separate issued paper - hard copy only)033-10997 A (separate issued paper - hard copy only)033-10998 A (separate issued paper - hard copy only)033-10999 A (separate issued paper - hard copy only)033-11000 A (separate issued paper - hard copy only)033-11001 A (separate issued paper - hard copy only)033-11002 A (separate issued paper - hard copy only)033-11003 A (separate issued paper - hard copy only)033-11004 A (separate issued paper - hard copy only)033-11005 A (separate issued paper - hard copy only)033-11006 A (separate issued paper - hard copy only)033-11007 A (separate issued paper - hard copy only)033-11008 A (separate issued paper - hard copy only)033-11009 A (separate issued paper - hard copy only)033-11010 A (separate issued paper - hard copy only)033-11011 A (separate issued paper - hard copy only)033-11012 A (separate issued paper - hard copy only)033-11013 A (separate issued paper - hard copy only)033-11014 A (separate issued paper - hard copy only)033-11015 A (separate issued paper - hard copy only)033-11016 A (separate issued paper - hard copy only)033-11021 A (separate issued paper - hard copy only)

033-11023 A (separate issued paper - hard copy only)033-11024 A (separate issued paper - hard copy only)033-11025 A (separate issued paper - hard copy only)033-11027 A (separate issued paper - hard copy only)033-11029 A (separate issued paper - hard copy only)033-11030 A (separate issued paper - hard copy only)033-11031 A (separate issued paper - hard copy only)033-11032 A (separate issued paper - hard copy only)033-11033 A (separate issued paper - hard copy only)033-11034 A (separate issued paper - hard copy only)033-11035 A (separate issued paper - hard copy only)033-11036 A (separate issued paper - hard copy only)033-11037 A (separate issued paper - hard copy only)033-11040 A (separate issued paper - hard copy only)033-11041 A (separate issued paper - hard copy only)033-11042 A 89033-11043 A 90033-11044 A 91033-11045 A 92033-11046 A 93033-11047 A 94033-11048 A 95033-11049 A 96033-11058 A 97033-11059 A 98033-11060 A 99033-11061 A (pag 1) 100033-11061 A (pag 2) 101033-11062 A 102033-11063 A 103033-11064 A 104033-11065 A 105033-11066 A 106033-11067 A 107033-11073 A 108033-11073 B 109033-11073 C 110033-11073 D 111033-11074 A 112033-11074 B 113033-11074 C 114033-11074 D 115033-11181 A 116033-11182 A 117033-11183 A 118033-11184 A 119

033-11185 A 120033-11186 A 121033-11187 A 122033-11188 A 123033-11189 A 124033-11190 A 125033-11191 A 126033-11192 A 127033-11193 A 128033-11194 A 129033-11195 A 130033-11196 A 131033-11198 A 132033-11201 A 133033-11202 A 134033-11204 A 135033-11204 B 136033-11204 C 137033-11207 A 138033-11207 B 139033-11208 A 140033-11209 A 141033-11209 B 142033-11210 A 143033-11210 B 144033-11211 A 145033-11211 B 146033-11212 A 147033-11212 B 148033-11213 A 149033-11213 B 150033-11214 A 151033-11214 B 152033-11215 A 153033-11216 A 154033-11223 A 155033-11223 B 156033-11223 C 157033-11224 A 158033-11224 B 159033-11224 C 160033-11226 A 161033-11226 B 162033-11228 A 163033-11229 A 164033-11231 A 165

033-11238 A 166033-11239 A 167033-11239 B 168033-11240 A 169033-11240 B 170033-11241 A 171033-11243 A 172033-11243 B 173033-11244 A 174033-11244 B 175033-11245 A 176033-11245 B 177033-11252 A 178033-11252 B 179033-11252 C 180033-11253 A 181033-11253 B 182033-11253 C 183033-11253 D 184033-11254 A 185033-11254 B 186033-11254 C 187033-11254 D 188033-11255 A 189033-11255 B 190033-11255 C 191033-11259 A 192033-11259 B 193033-11260 A 194033-11260 B 195033-11261 A 196033-11262 A 197033-11270 A 198033-11271 A 199033-11272 A 200033-11702 A 201033-11704 A 202033-11717 A 203033-12275 A 204033-12276 A 205033-12277 A 206033-12280 A 207033-12281 A 208033-12285 A 209033-12289 A 210033-12302 A 211

033-12302 B 212033-12303 A 213033-12303 B 214033-12304 A 215033-12305 A 216033-12306 A 217033-12306 B 218033-12307 A 219033-12307 B 220033-12308 A 221033-12308 B 222033-12309 A 223033-12309 B 224033-12310 A 225033-12311 A 226033-12312 A 227033-12313 A 228033-12314 A 229033-12315 A 230033-12316 A 231033-12317 A 232033-12318 A 233033-12319 A 234033-12320 A – 033-12328A 235033-12329 A – 033-12338 A 236033-12339 A 237033-12340 A 238033-12341 A 239033-12342 A 240033-12343 A 241033-12344 A 242033-12345 A 243033-12346 A 244033-12347 A, 033-12348 A 245033-12349 A 246033-12350 A, 033-12351 A 247033-12353 A (separate issued paper - hard copy only)033-12354 A (separate issued paper - hard copy only)033-12355 A (separate issued paper - hard copy only)033-12356 A (separate issued paper - hard copy only)033-12359 A – 033-12361 A 248033 12364 A – 033-12366 A 249033 12367 A 250033-12368 A (separate issued paper - hard copy only)033-12369 A (separate issued paper - hard copy only)033-12370 A (separate issued paper - hard copy only)

033-12371 A (separate issued paper - hard copy only)033-12372 A (separate issued paper - hard copy only)033-12373 A (separate issued paper - hard copy only)033-12374 A (separate issued paper - hard copy only)033-12375 A (separate issued paper - hard copy only)033-12376 A (separate issued paper - hard copy only)033-12377 A (separate issued paper - hard copy only)

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CIVIL AVIATION AUTHORITYFLIGHT PLANNING & MONITORING

DATA SHEET MEP1

6. DESCENTMethod of Use.

1. Enter graph with OAT at cruise altitude and move vertically to cruise altitude.2. From there move horizontally to fuel, time and distance lines.3. Move vertically down respectively from each and read values for fuel (gallons), time (minutes)

and distance (nautical miles).4. Repeat 1,2 and 3 for altitude of airfield.5. Subtract results of 4 from 3 and derive fuel, time and distance for descent profile.

Figure 3.6 DESCENT

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CIVIL AVIATION AUTHORITYFUEL PLANNING

DATA SHEET MRJT 1

Figure 4.5.3.1 Long Range CruiseAll Engines Maximum Cruise Thrust Limits A/C Auto

PRESSURE ALTITUDE 33000 Ft.

NOTE - OPTIMUM WEIGHT FOR PRESSURE ALTITUDE IS 58200 KGTHRUST LIMITED WEIGHT FOR ISA + 10 AND COLDER EXCEEDS STRUCTURAL LIMIT

THRUST LIMITED WEIGHT FOR ISA + 15 THRUST LIMITED WEIGHT FOR ISA + 20

EXCEEDS STREXCEEDS STRUCTURAL LIMITIS66400 KG

ADJUSTMENTS FOR OPERATION AT NON-STANDARD TEMPERATURES-

INCREASE FUEL REQUIRED BYDECREASE FUEL REQUIRED BY

0.6 PERCENT PER 10 DEGREES C ABOVE ISA0.6 PERCENT PER 10 DEGREES C BELOW ISA

INCREASE TAS BY 1 KNOT PER DEGREE C ABOVE ISADECREASE TAS BY 1 KNOT PER DEGREE C BELOW ISA

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DATA SHEET MRJT 1

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JAA Appendices, Subject: 010 Page Edition:12-2002

NOTE - OPTIMUM WEIGHT FOR PRESSURE ALTITUDE EXCEEDS STRUCTURAL LIMITTHRUST LIMITED WEIGHT FOR ISA + 10 AND COLDER EXCEEDS STRUCTURAL LIMIT

EXCEEDS STRUCTURAL LIMITEXCEEDS STRUCTURAL LIMIT

INCREASE FUEL REQUIRED BY DECREASE FUEL REQUIRED BY

DATA SHEET MRJT 1

Figure 4.5.1 EN – ROUTE CLIMB 280/.74 ISA -6° C TO -15° C

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DATA SHEET MRJT 1

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DATA SHEET MRJT 1

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CIVIL AVIATION AUTHORITY FUEL PLANNING

DATA SHEET MRJT 1

NOTE - OPTIMUM WEIGHT FOR PRESSURE ALTITUDE IS 53200 KGTHRUST LIMITED WEIGHT FOR ISA + 10 AND COLDER IS 64500 KG

THRUST LIMITED WEIGHT FOR ISA + 15THRUST LIMITED WEIGHT FOR ISA + 20

IS 63100 KGIS 61400 KG

0.6 PERCENT PER 10 DEGREES C ABOVE ISA

0.6 PERCENT PER 10 DEGREES C BELOW ISA

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DATA SHEET MRJT 1

Figure 4.2.1 OPTIMUM ALTITUDE

Figure 4.2.2 SHORT DISTANCE CRUISE ALTITUDE

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DATA SHEET MRJT 1

Figure 4.5.3.2 Mach 0.74 CruiseAll Engines Maximum Cruise Thrust Limits A/C Auto

PRESSURE ALTITUDE 22000Ft TAS 451 Kts

NOTE - OPTIMUM WEIGHT FOR PRESSURE ALTITUDE EXCEEDS STRUCTURAL LIMIT HRUST LIMITED WEIGHT FOR ISA + 10 AND COLDER EXCEEDS STRUCTURAL LIMIT

ADJUSTMENTS FOR OPERATION AT NON-STANDARD TEMPERATURES- INCREASE FUEL REQUIRED BY

DECREASE FUEL REQUIRED BY 0.6 PERCENT PER 10 DEGREES C ABOVE ISA

0.6 PERCENT PER 10 DEGREES C BELOW ISA INCREASE TAS BY 1 KNOT PER DEGREE C ABOVE ISA

DECREASE TAS BY 1 KNOT PER DEGREE C BELOW ISA

33-3320 C

DATA SHEET MRJT 1

Figure 4.5.3.2 Mach 0.74 Cruise

All Engines Maximum Cruise Thrust Limits A/C Auto PRESSURE ALTITUDE 25000Ft TAS 445 Kts

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Figure 4.3.1B SIMPLIFIED FLIGHT PLANNING

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DATA SHEET MRJT 1

3.3 Alternate Planning (Fig. 4.3.6)The fuel and time figures extracted from this chart include the following:Ÿ Missed approachŸ Climb to cruise altitudeŸ Cruise at LRCŸ Descent and straight on approach.Method of use is similar to previous graphs.For distances greater than 500 NM use the LRC Simplified Flight Planning Charts.

Figure 4.3.6 SIMPLIFIED FLIGHT PLANNING ALTERNATE PLANNING LONG RANGE CRUISE

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DATA SHEET MRJT 1

Figure 4.3.3C SIMPLIFIED FLIGHT PLANNING

0.78 MACH CRUISE

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DATA SHEET MRJT 1

4. HOLDING FUEL PLANNING

The table below provides fuel flow Information necessary for planning holding reserve fuel requirements.Chart is based on racetrack pattern at minimum drag airspeed - minimum speed 210KIAS.For holding in straight and level reduce table values by 5%

Figure 4.4FLAPS UP

Fuel flow is based on a racetrack pattern.For holding in straight and level flight reduce fuel values by 5%

5. DETAILED FUEL PLANNING 5.1 En-route Climb (Figures 4.5.1)Tables are provided for a range of temperature deviations from ISA -15°C to ISA +25°CFuel and time given in these tables are from brake release and distance from 1500 ft. with a climb airspeed schedule 280 KIAS/0.74 Mach. The stated TAS is the average for the climb and should be used to correct the still air distance shown.

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CIVIL AVIATION AUTHORITYFUEL PLANNING & MONITORING

DATA SHEET MEP1

3. RANGE AT STANDARD TEMPERATURES Method of Use

1. Enter graph (Fig.3.2) with cruise altitude2. Move horizontally to power selected intersection (with or without reserve)3. Move vertically to read range in nautical miles still air distance.

Figure 3.2 RANGE

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DATA SHEET MRJT 1

4. HOLDING FUEL PLANNINGThe table below provides fuel flow Information necessary for planning holding reserve fuel requirements.Chart is based on racetrack pattern at minimum drag airspeed - minimum speed 210KIAS.For holding in straight and level reduce table values by 5%

Figure 4.4FLAPS UP

5. DETAILED FUEL PLANNING 5.1 En-route Climb (Figures 4.5.1)

Tables are provided for a range of temperature deviations from ISA -15°C to ISA +25°CFuel and time given in these tables are from brake release and distance from 1500 ft. with a climb airspeed schedule 280 KIAS/0.74 Mach. The stated TAS is the average for the climb and should be used to correct the still air distance shown.

033-3911 B CIVIL AVIATION AUTHORITYFUEL PLANNING

DATA SHEET MRJT 1

3.3 Alternate Planning (Fig. 4.3.6)The fuel and time figures extracted from this chart include the following:Ÿ Missed approachŸ Climb to cruise altitudeŸ Cruise at LRCŸ Descent and straight on approach.

Method of use is similar to previous graphs.For distances greater than 500 NM use the LRC Simplified Flight Planning Charts

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DATA SHEET MRJT 1

Figure 4.3.2A SIMPLIFIED FLIGHT PLANNING

0.74 MACH CRUISE

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DATA SHEET MRJT 1

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DATA SHEET MEP 1

4. POWER SETTING, FUEL FLOW AND TASEnter the power setting table (fig. 3.3) with required % power to obtain fuel flow in US gallons per hour.Manifold Pressure is read off against pressure altitude and RPM in the correct % power column.Figure 3.3 POWER SETTING TABLE

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DATA SHEET MEP 1

4. POWER SETTING, FUEL FLOW AND TASEnter the power setting table (fig. 3.3) with required % power to obtain fuel flow in US gallons per hour.Manifold Pressure is read off against pressure altitude and RPM in the correct % power column.

Figure 3.3 POWER SETTING TABLE

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DATA SHEET MEP 1

5. ENDURANCE PROFILEThe graph at Figure 2.5 (page 1) provides a rapid method for determination of endurance for the sample aeroplane. An example is shown on the graph.

Figure 2.5 ENDURANCE

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DATA SHEET SEP 1

Figure 2.2 RECOMMENDED CRUISE POWER SETTINGSTABLE 2.2.3

20° C LEAN 23.0 IN. HG (OR FULL THROTTLE) @ 2300 RPM

Of Peak EGT CRUISE LEAN MIXTURE 3400 Ibs.

Press. Alt.

IOAT Man. Press.

Fuel Flow Air Speed

Feet °C °F IN. HG PPH GPH KIAS KTASISA - 20° C(ISA - 36° F)

0 2000 4000 6000 8000

10,000 12,000 14,000 16.000

-11 -15 -18 -23 -17 -31 -35

26 20 13

6 -1 -9

-16 -23 -31

23.0 23.0 23.0 23.0 22.4 20.7 19.2 17.8 16.4

67.6 69.7 72.1 74.4 73.8 68.4 63.8 60.0 56.3

11.3 11.6 12.0 12.4 12.3 11.4 10.6 10.0

152 152 153 153 150 143 135 127 117

144 149 154 158

160 157 153 148 141

Standard Day (ISA)

0 2000 4000 6000 8000

10,000 12,000 14,000 16.000

-11 -15

62 56 49 42 35 27 20 13

23.0 23.0 23.0 23.0 22.4 20.7 19.2 17.8 16.4

65.4 67.4 69.4 71.7 71.1 66.2 61.8 58.5 55.3

10.9 11.2 11.6 12.0 11.9 11.0 10.3

9.8 9.2

147 147 148 148 145 137 129 120 109

145 149 154 159 160 157 152 146 137

ISA + 20° C(ISA + 36° F)

0 2000

4000 6000 8000

10,000

12,000

14,000

16,000

37 33 29 25 22 17 13

98 92 85 78 71 63 56 48

23.0 23.0 23.0 23.0 22.4 20.7 19.2 17.8

63.2 65.1 67.1 69.0 68.5 64.0 60.0 57.1

10.5 10.9 11.2 11.5 11.4 10.7 10.0

142 143 143 142 140 132 123 113

145 149 154 158 160 156 151 142

NOTES: 1. Full throttle manifold pressure settings are approximate.2. Shaded area represents Operation with full throttle.3. Fuel flows are to be used for flight planning only and will vary from

aeroplane to aeroplane. Lean using the EGT.

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DATA SHEET MRJT 1

4. HOLDING FUEL PLANNINGThe table below provides fuel flow Information necessary for planning holding reserve fuel requirements.Chart is based on racetrack pattern at minimum drag airspeed - minimum speed 210KIAS.For holding in straight and level reduce table values by 5%

Figure 4.4FLAPS UP

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1 AEROPLANE DATA AND CONSTANTS1.1 Aeroplane Data

· Monoplane · Twin turbo-jet engines · Retractable undercarriage

Structural Limits: - Maximum Taxi (Ramp) Mass Maximum Take Off Mass Maximum Landing Mass Maximum Zero Fuel Mass Maximum Fuel Load

63060 Kg. 62800 Kg. 54900 Kg. 51300 Kg. 5311 U.S. Gallons 16145 Kg. (@ 3.04 Kg./Gal.)

1.2 Constants Fuel Density (unless otherwise notified) 3.04 Kg./US Gallon 6.7 Ibs AIS Gallon 2. OPTIMUM ALTITUDES

2.1 Optimum Cruise Altitude (Fig. 4.2.1)Enter graph with cruise mass (56800 Kg.) Move vertically to selected cruise profile (LRC) Move horizontally to read optimum altitude (33500 ft.)NB. Fuel Penalties will be incurred by operating "off optimum" altitude as shown in table.

OFF - OPTIMUM CONDITION FUEL MILEAGE PENALTY %LRC 0.74

2000 n. above Optimum 2000 n below 4000 ft. below 8000 ft. below 12000 ft. below

1 0 1 4

1 0 2 4 11 20

2.2 Short Distance Cruise Altitude (Fig. 4.2.2)Enter with trip distance (Nautical Air Miles).Move to temperature deviation.Move horizontally to reference line.Follow the trade lines to intersect with vertical through brake release weight.Move horizontally to read maximum pressure altitude.

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ENDURANCE/FUEL CALCULATION

Fuel (kg) Time (hh:mm)

Trip FuelContingency FuelAlternate FuelFinal Reserve Fuel

18001325

Minimum T/O-FuelExtra Fuel

Actual T/O-Fuel Taxi FUEL 200

Ramp Fuel 10000

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DATA SHEET MRJT 1

IS 63100 KGIS 61400 KG

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Figure 4.5.1 EN - ROUTE CLIMB 280/.74 ISA +6° C TO +15° C

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JAA Appendices, Subject: 010 Page Edition:12-2002

INCREASE FUEL REQUIRED BY DECREASE FUEL REQUIRED BY

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IS 63100 KGIS 61400 KG

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033-9579 C CIVIL AVIATION AUTHORITYFUEL PLANNING

DATA SHEET MRJT 1

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DATA SHEET MRJT 1

PRESSURE ALTITUDE 34000 Ft TAS 428 Kts

NOTE - OPTIMUM WEIGHT FOR PRESSURE ALTITUDE IS 55500 KG THRUST LIMITED WEIGHT FOR ISA + 10 AND COLDER IS 67100 KG

IS 65700 KGIS 64000 KG

INCREASE TAS BY 1 KNOT PER DEGREE C ABOVE ISA DECREASE TAS BY 1 KNOT PER DEGREE C BELOW ISA

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Figure 4.3.1B SIMPLIFIED FLIGHT PLANNING

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Figure 4.3.3C SIMPLIFIED FLIGHT PLANNING

0.78 MACH CRUISE

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Figure 4.4FLAPS UP

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Figure 4.4FLAPS UP

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Figure 4.4FLAPS UP

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DATA SHEET MRJT 1

5.4 DescentThese tables (Fig. 4.5.4) provide tabulations of time, fuel and distance for "flight idle" thrust at 0.74 mach/250 KIAS (economy) and 0.70 Mach/280 KIAS (turbulence penetration)Allowances are made for a straight in approach with gear down. Figure 4.5.4 Descent .74M/250 KIAS

.70M/280/250 KIAS

BASED ON IDLE THRUST. ALLOWANCES FOR A STRAIGHT-IN APPROACH ARE INCLUDED.

033-9705 A CIVIL AVIATION AUTHORITYFUEL PLANNING

DATA SHEET MRJT 1

5.4 DescentThese tables (Fig. 4.5.4) provide tabulations of time, fuel and distance for "flight idle" thrust at 0.74 mach/250 KIAS (economy) and 0.70 Mach/280 KIAS (turbulence penetration)Allowances are made for a straight in approach with gear down. Figure 4.5.4 Descent.74M/250 KIAS

.70M/280/250 KIAS

BASED ON IDLE THRUST.ALLOWANCES FOR A STRAIGHT-IN APPROACH ARE INCLUDED.

DATA SHEET MRJT 1

5.4 DescentThese tables (Fig. 4.5.4) provide tabulations of time, fuel and distance for "flight idle" thrust at 0.74 mach/250 KIAS (economy) and 0.70 Mach/280 KIAS (turbulence penetration)Allowances are made for a straight in approach with gear down. Figure 4.5.4 Descent.74M/250 KIAS

.70M/280/250 KIAS

BASED ON IDLE THRUST. ALLOWANCES FOR A STRAIGHT-IN APPROACH ARE INCLUDED.

033-9707 B

NOT FOR NAVIGATIONALPURPOSES!

COPYRIGHT !JEPPESEN GMBH EDITION NOVEMBER ' 99

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DATA SHEET SEP 1

FIGURE 2.1 TIME FUEL AND DISTANCE TO CLIMB

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DATA SHEET SEP 1

4. RANGE PROFILEThe graph at Figure 2.4 (page 9) provides a simple and rapid means of determining the still air range (nautical air miles) for the sample aeroplane. An example of the use of the graph is shown.Note that the figures make allowance for the taxi, run-up and 45 minutes reserve fuel.

Figure 2. 4 RANGE

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DATA SHEET SEP 1

Figure 2.2 RECOMMENDED CRUISE POWER SETTINGSTABLE 2.2.2

Press. Alt.

IOATMan.

Press.Fuel Flow

Air Speed

Feet °C °F IN. HG PPH GPH KIAS KTAS

ISA - 20° C(ISA - 36° F)

0 2000 4000 6000 8000

10,000 12,000 14,000 16.000

-11 -15 -19 -23 -27 -31 -35

26 19 12

5 -2 -9

-17 -24 -32

25.0 25.0 25.0 24.3 22.5 20.8

19.3 17.9 16.5

63.8 66.4 68.9 68.3 63.9 60.1 56.7 54.5 52.2

10.6 11.1 11.5 11.4 10.7 10.0

9.5 9.1 8.7

148 149 149 147 139 132 123 113

140 145 150 152

148 144 139 132 114

Standard Day (ISA)

0 2000 4000 6000 8000

10,000 12,000 14,000 16.000

62 55 48

41 34 27 19 12

25.0 25.0 25.0 24.3 22.5 20.8

19.3 17.9

61.9 64.2 66.6 66.1 61.9 58.5 55.6 53.5

10.3 11.7 11.1 11.0 10.3

9.8 9.3 8.9

143 143 144 141 134 126 116 103

140145150152148 143136125

ISA + 20° C(ISA + 36° F)

0 2000 4000 6000 8000

10,000 12,000 14,000 16.000

37 33 29 25 21 17 13

98 91 84 77 70 63 55

25.0 25.0 25.0 24.3 22.5 20.8

19.3 - -

60.1 62.1 64.4 63.9 60.2 56.8

54.5 - -

10.0 10.4 10.7 10.7 10.0

9.5 9.1

138 138 139 136 128 119 108

140 145 150 151 147 141 131

NOTES: 1. Full throttle manifold pressure settings are approximate.

2. Shaded area represents operation with full throttle.3. Fuel flows are to be used for flight planning only and will vary from aeroplane

to aeroplane. Lean using the EGT.

033-9733 A

DATA SHEET SEP 1

Figure 2.2 RECOMMENDED CRUISE POWER SETTINGS

TABLE 2.2.3

Press. Alt.

IOATMan.

Press.Fuel Flow

Air Speed

Feet °C °F IN. HG PPH GPH KIAS KTAS

ISA - 20° C(ISA - 36° F)

0 2000 4000 6000 8000

10,000 12,000 14,000 16.000

-11-15-18-23-17-31-35

26 20 13

6 -1 -9

-16 -23 -31

23.0 23.0 23.0 23.0 22.4 20.719.2 17.8 16.4

67.6 69.7 72.1 74.4 73.868.463.860.056.3

11.3 11.6 12.0 12.4 12.3 11.4 10.610.0

152152153153150143135127117

144149154158160 157153148141

Standard Day (ISA)

0 2000 4000 6000 8000

10,000 12,000 14,000 16.000

-11-15

62 56 49 42 35 27 20 13

23.0 23.0 23.023.022.420.719.217.816.4

65.4 67.469.471.771.166.261.858.555.3

10.9 11.211.612.011.911.010.3

9.89.2

147 147 148 148 145 137 129 120 109

145 149 154 159 160 157 152 146 137

ISA + 20° C(ISA + 36° F)

0 2000 4000 6000 8000

10,000 12,000 14,000 16.000

37 33 29 25 22 17 13

98 92 85 78 71 63 56 48

23.023.0 23.0 23.0 22.4 20.7 19.2 17.8

63.265.1 67.1 69.0 68.5 64.0 60.0 57.1

10.510.9 11.2 11.5 11.4 10.7 10.0

142 143 143 142 140 132 123 113

145 149 154 158 160 156 151 142

NOTES: 1. Full throttle manifold pressure settings are approximate.2. Shaded area represents Operation with full throttle. 3. Fuel flows are to be used for flight planning only and will vary from aeroplane to

aeroplane. Lean using the EGT.

033-11042 A

03-11043 A

033-11044 A

033-11045 A

033-11046 A

033-11047 A

033-11048 A

033-11049 A

033-11058 A NOT FOR NAVIGATIONALPURPOSES!

033-11061 A (pag. 1) NOT FOR NAVIGATIONALPURPOSES!

033-11061 A (pag. 2)

033-11067 A

033-11073 A

JAR - FCLFLIGHT PLANNING

QUICK DETERMINATION OF FLIGHT PLAN

INTRODUCTION

The following flight planning tables allow the planner to determine trip fuel consumption and trip time required to cover a given air distance. These tables are established for:- Takeoff - Climb profile : 250kt/300kt/M.80 - Cruise mach number: M.80, M.82, M.84, LR - Descent profile: Cruise Mach number/300kt/250kt - Approach and landing : 240 kg - 6 minute IFR -ISA - CG = 37 % - Normal air conditioning -Anti ice OFFNote:

1. In the tables, the asterisk (*} means that a step climb of 4000 feet must be flown to reach the corresponding FL.

2. To obtain a flight plan at optimum cruise level, the highest flight level desired within the flight has to be selected in the table.

3. For each degree Celsius above ISA temperature apply fuel correction 0.010 (kg/°C/NM) x ISA(°C) x Air Distance (NM).

CORRECTION FOR DEVIATION FROM REFERENCE LANDING WEIGHT

The fuel consumption must be corrected when the actual landing weight is different from the reference landing weightIf it is lover (or greater) man the reference landing weight subtract (or add) the value given in the correction part of the table per 1000 kg below (or above) the reference landing weight.

033-11073 B

DATA SHEET LRJT 1

FLIGHT PLANNING GROUND DISTANCE/AIR DISTANCE

033-11073 C

DATA SHEET LRJT 1

FLIGHT PLANNING QUICK DERTERMINATION OF F-PLN

033-11073 D

DATA SHEET LRJT 1

033-11074 AJAR - FCL FLIGHT PLANNING

INTRODUCTION

The following flight planning tables allow the planner to determine trip fuel consumption and trip time required to cover a given air distance. These tables are established for:- Takeoff - Climb profile : 250kt/300kt/M.80 - Cruise mach number: M.80, M.82, M.84, LR - Descent profile: Cruise Mach number/300kt/250kt - Approach and landing : 240 kg - 6 minute IFR -ISA - CG = 37 % - Normal air conditioning -Anti ice OFFNote:

033-11074 B

DATA SHEET LRJT 1

FLIGHT PLANNING GROUND DISTANCE/AIR DISTANCE

033-11074 C

DATA SHEET LRJT 1

033-11074 D

DATA SHEET LRJT 1

033-11181 A

033-11182 A

033-11183 A

033-11184 A

033-11185 A

033-11186 A

033-11187 A

033-11188 A

033-11189 A

033-11190 A

033-11191 A

033-11192 A

033-11193 A

033-11194 A

033-11195 A

List of TAFsTAF EDDF ISSUED AT 042200 EDDF 0524 VRE03KT CAVOK BECMG 0609 20005KT 9999 SCT030 BKN045 =

TAF EDDK ISSUED AT 042200 EDDK 0624 14005KT 7000 NSC BECMG 0608 CAVOK TEMPO 1115 9999 SCT040 = TAF EDDL ISSUED AT 042200 EDDL 0624 16003KT 5000 NSC BECMG 0608 CAVOK = TAF EDDM TSSUED AT 042200 EDCM 0624 26005KT 9999 SCT035 =

TAF EDDN ISSUED AT 042200 EDDN 0624 26005KT 9999 SCT035 = TAF EDDH ISSUED AT 042200 EDOH 0624 21010KT CAVOK BECMG 0810 9999 SCT025 SCT040 PROB30 TEMPO 1218 7000 -RADZ BKN012 BECMG 1620 7000 BKN020 TEMPO 1824 4000 RADZ BKN005 =

TAF EDDS ISSUED AT 042200 EDDS 0624 26005KT 9999 SCT035 =

TAF EGLL ISSUED AT 042200 EGLL 0624 17005KT 5000 SCT040 PROB30 TEMPO 0607 1500 BR BECMG 0811 23010KT 9999 BECMG 1619 BRNO15 =

TAF EHAM ISSUED AT 042200 EHAM 0624 VRB03KT CAVOK BECMG 0710 21009KT SCT025 BKN080 PROB30 TEMPO 1218 7000 BR -RA SCT012 SCT035 BECMG 1215 27012KT BECMG 2023 6000 BR SCT008 =

TAF EHBK ISSUED AT 040400 EHBK 1206 28011KT 7000 BR SCT012 SCT040 BECMG 1215 CAVOK BECMG 1720 VRB03KT BECMG 0104 20006KT 7000 BR SCT008 BKN012 =

033-11196 A

List of TAFsTAF EDDF ISSUED AT 042200EDDF 0524 VRE03KT CAVOKBECMG 0609 20005KT 9999 SCT030 BKN045 =

TAF EDDK ISSUED AT 042200 EDDK 0624 14005KT 7000 NSC BECMG 0608 CAVOK TEMPO 1115 9999 SCT040 = TAF EDDL ISSUED AT 042200 EDDL 0624 16003KT 5000 NSC BECMG 0608 CAVOK = TAF EDDM TSSUED AT 042200EDCM 0624 26005KT 9999 SCT035 =

TAF EDDN ISSUED AT 042200EDDN 0624 26005KT 9999 SCT035 = TAF EDDH ISSUED AT 042200EDOH 0624 21010KT CAVOKBECMG 0810 9999 SCT025 SCT040PROB30 TEMPO 1218 7000 -RADZ BKN012BECMG 1620 7000 BKN020TEMPO 1824 4000 RADZ BKN005 =

TAF EDDS ISSUED AT 042200EDDS 0624 26005KT 9999 SCT035 =

TAF EHAM ISSUED AT 042200EHAM 0624 VRB03KT CAVOKBECMG 0710 21009KT SCT025 BKN080PROB30 TEMPO 1218 7000 BR -RA SCT012 SCT035BECMG 1215 27012KTBECMG 2023 6000 BR SCT008 =

TAF EHBK ISSUED AT 040400EHBK 1206 28011KT 7000 BR SCT012 SCT040BECMG 1215 CAVOKBECMG 1720 VRB03KTBECMG 0104 20006KT 7000 BR SCT008 BKN012 =

033-11198 A

List of TAFsTAF EDDF ISSUED AT 042200EDDF 0524 VRE03KT CAVOKBECMG 0609 20005KT 9999 SCT030 BKN045 =

TAF EDDK ISSUED AT 042200 EDDK 0624 14005KT 7000 NSC BECMG 0608 CAVOK TEMPO 1115 9999 SCT040 = TAF EDDL ISSUED AT 042200 EDDL 0624 16003KT 5000 NSC BECMG 0608 CAVOK = TAF EDDM TSSUED AT 042200EDCM 0624 26005KT 9999 SCT035 =

TAF EDDN ISSUED AT 042200EDDN 0624 26005KT 9999 SCT035 = TAF EDDH ISSUED AT 042200EDOH 0624 21010KT CAVOKBECMG 0810 9999 SCT025 SCT040PROB30 TEMPO 1218 7000 -RADZ BKN012BECMG 1620 7000 BKN020TEMPO 1824 4000 RADZ BKN005 =

TAF EDDS ISSUED AT 042200EDDS 0624 26005KT 9999 SCT035 =

TAF EHAM ISSUED AT 042200EHAM 0624 VRB03KT CAVOKBECMG 0710 21009KT SCT025 BKN080PROB30 TEMPO 1218 7000 BR -RA SCT012 SCT035BECMG 1215 27012KTBECMG 2023 6000 BR SCT008 =

TAF EHBK ISSUED AT 040400EHBK 1206 28011KT 7000 BR SCT012 SCT040BECMG 1215 CAVOKBECMG 1720 VRB03KTBECMG 0104 20006KT 7000 BR SCT008 BKN012 =

033-11201 A

033-11202 A

033-11204 A

INTRODUCTION

The following flight planning tables allow the planner to determine trip fuel consumption and trip time required to cover a given air distance. These tables are established for:- Takeoff- Climb profile : 250kt/300kt/M.80- Cruise mach number: M.80, M.82, M.84, LR- Descent profile: Cruise Mach number/300kt/250kt- Approach and landing : 240 kg - 6 minute IFR- ISA- CG = 37 %- Normal air conditioning- Anti ice OFFNote:

033-11204 B

DATA SHEET LRJT 1

JAR - FCL FLIGHT PLANNING GROUND DISTANCE/AIR DISTANCE

LONG RANGE CRUISE ABOVE FL250

033-11204 C

GROUND DISTANCE/AIR DISTANCE

033-11207 A DATA SHEETLRJT 1

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuel price ratio between departure and destination airports. The following pages present for one flight level per page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel price divided by destination fuel price) and on the air distance to fly.The computed optimum takeoff weight is based on the additional fuel consumption needed for the transport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. The quantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoff weight (including extra fuel) and the planned takeoff weight {without fuel tanking). The graphs are established for:- FL 290, 310, 330, 350, 370, 390- Air distances from 500 to 5000 NM- Flight profile :Climb 250kt/300kt/M.80Cruise M.80Descent M.80/300kt/250ktNote:

1. ff necessary, step climbs are performed to reach the indicated flight levels.2. The crew/operator has to verify that the found aircraft weight complies with basic aircraft

limitations (e.g. max fuel capacity) as well as with mission dependent restrictions (e.g. MLW at destination).

EXAMPLES1. Fuel price ratio = 0.930 Cruising Altitude = FL310 Planned TOW = 200 000 kg (mission weight without fuel tanking) Air Distance = 2500 NM Enter graph For the given air distance, the optimum fuel tanking weight is 187 000 kg, which is lower than the planned takeoff weight d no fuel tanking recommended.2. fuel price ratio = 0.890Cruising Altitude = FL 350 Planned TOW = 190 000 kg (mission weight without fuel tanking) Air Distance = 3250 NM Enter graph For the given air distance, the optimum fuel tanking weight is 198 000 kg, which is 8 000 kg higher than the planned takeoff weight d optimum quantity of extra fuel is 8 000 kg.

Check : a) new TOW less or equal MTOW from departure airport. b) total fuel to be loaded less or equal maximum fuel capacity. c) MLW at destination

033-11207 B

DATA SHEET LRJT 1

FUEL TANKING

033-11208 A

DATA SHEET LRJT 1

FUEL TANKING

033-11209 A

DATA SHEETLRJT 1

FUEL TANKING

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310 Planned TOW = 200 000 kg (mission weight without fuel tanking) Air Distance = 2500 NM Enter graph For the given air distance, the optimum fuel tanking weight is 187 000 kg, which is lower than the planned take off weight d no fuel tanking recommended.2. fuel price ratio = 0.890Cruising Altitude = FL 350 Planned TOW = 190 000 kg (mission weight without fuel tanking) Air Distance = 3250 NM Enter graph For the given air distance, the optimum fuel tanking weight is 198 000 kg, which is 8 000 kg higher than the planned takeoff weight optimum quantity of extra fuel is 8 000 kg. Check : a) new TOW less or equal MTOW from departure airport. b) total fuel to be loaded less or equal maximum fuel capacity.

c) MLW at destination

033-11209 B

DATA SHEET LRJT 1

JAR - FCL FLIGHT PLANNING FUEL TANKING

033-11210 A

DATA SHEETLRJT 1

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuel price ratio between departure and destination airports. The following pages present for one flight level per page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel price divided by destination fuel price) and on the air distance to fly.The computed optimum takeoff weight is based on the additional fuel consumption needed for the transport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. The quantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoff weight (including extra fuel) and the planned takeoff weight {without fuel tanking).

The graphs are established for:- FL 290, 310, 330, 350, 370, 390- Air distances from 500 to 5000 NM- Flight profile : Climb 250kt/300kt/M.80 Cruise M.80 Descent M.80/300kt/250ktNote: 1. ff necessary, step climbs are performed to reach the indicated flight levels. 2. The crew/operator has to verify that the found aircraft weight complies with basic aircraft limitations (e.g. max fuel capacity) as well as with mission dependent restrictions (e.g. MLW at destination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking) Air Distance = 2500 NM Enter graphFor the given air distance, the optimum fuel tanking weight is 187 000 kg, which is lower than the planned takeoff weight d no fuel tanking recommended.2. fuel price ratio = 0.890Cruising Altitude = FL 350Planned TOW = 190 000 kg (mission weight without fuel tanking) Air Distance = 3250 NM Enter graphFor the given air distance, the optimum fuel tanking weight is 198 000 kg, which is 8 000 kg higher than the planned takeoff weight d optimum quantity of extra fuel is 8 000 kg. Check :a) new TOW less or equal MTOW from departure airport.b) total fuel to be loaded less or equal maximum fuel capacity.c) MLW at destination

033-11210 B

DATA SHEETLRJT 1

FUEL TANKING

033-11211 A

INTRODUCTION

033-11211 B

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNING QUICK DERTERMINATION OF F-PLN

033-11212 A

JAR - FCL FLIGHT PLANNING QUICK DETERMINATION OF FLIGHT PLAN

INTRODUCTION

033-11212 B

033-11213 A

INTRODUCTION

033-11213 B

033-11214 A

INTRODUCTION

033-11214 B JAR - FCL FLIGHT PLANNING

QUICK DERTERMINATION OF F-PLN

0 33-11215 A DATA SHEETLRJT 1

INTEGRATED CRUISE

033-11216 A

DATA SHEETLRJT 1

INTEGRATED CRUISE

033-11223 A

DATA SHEETLRJT 1

INTEGRATED CRUISE

033-11223 B

DATA SHEETLRJT 1

INTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tables with the numbers given in the following tables. The tables which are established for M.80, M.82, M.84 and long range speed take into account climbing from the brake release point at 250KT/300KT/M.80.

LONG RANGE SPEED

CLIMB TO OPTIMUM FL

STEP CLIMB CORRECTION

When the flight includes one or more step climbs (2000 feet below FL290, 4000 feet above), apply a correction of 160 kg per step climb to the fuel consumption.

033-11223 C

DATA SHEETLRJT 1

INTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables as follows to take into account the descent down to 1500 feet followed by 6 min IFR approach and landing.

LONG RANGE CRUISE

IRC, M.80, M.82. M.84 FROM OPTIMUM FL

033-11224 A

DATA SHEETLRJT 1

INTEGRATED CRUISE

033-11224 B

DATA SHEETLRJT 1

INTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tables with the numbers given in the following tables. The tables which are established for M.80, M.82, M.84 and long range speed take into account climbing from the brake release point at 250KT/300KT/M.80. LONG RANGE SPEED

CLIMB TO OPTIMUM FL

033-11224 C

DATA SHEETLRJT 1

INTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take into account the descent down to 1500 feet followed by 6 min IFR approach and landing.

LONG RANGE CRUISE

033-11226 A

DATA SHEET LRJT 1

JAR - FCLFLIGHT PLA

CRUISE LEVEL

033-11226 B DATA SHEET LRJT 1

JAR - FCLFLIGHT PL

CRUISE LEVEL

033-11228 A DATA SHEET LRJT 1

033-11229 A DATA SHEET LRJT 1

JAR - FCLFLIGHT PLA

CRUISE LEVEL

033-11231 A

DATA SHEET LRJT 1

033-11238 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNING INTERGRATED CRUISE

033-11239 A

DATA SHEETLRJT 1

FUEL TANKING

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310 Planned TOW = 200 000 kg (mission weight without fuel tanking) Air Distance = 2500 NM Enter graph For the given air distance, the optimum fuel tanking weight is 187 000 kg, which is lower than the planned takeoff weight d no fuel tanking recommended.2. fuel price ratio = 0.890Cruising Altitude = FL 350 Planned TOW = 190 000 kg (mission weight without fuel tanking) Air Distance = 3250 NM Enter graph For the given air distance, the optimum fuel tanking weight is 198 000 kg, which is 8 000 kg higher than the planned takeoff weight d optimum quantity of extra fuel is 8 000 kg. Check : a) new TOW less or equal MTOW from departure airport. b) total fuel to be loaded less or equal maximum fuel capacity. c) MLW at destination

033-11239 B DATA SHEETLRJT 1

FUEL TANKING

JAR - FCL FLIGHT PLANNING INTERGRATED CRUISE

FUEL TANKING

033-11244 B

DATA SHEETLRJT 1

033-11245 A

DATA SHEETLRJT 1

FUEL TANKING

033-11252 A

DATA SHEETLRJT 1

INTERGRATED CRUISE

033-11252 B

DATA SHEETLRJT 1

INTEGRATED CRUISE

CLIMB CORRECTION

LONG RANGE SPEED

CLIMB TO OPTIMUM FL

033-11252 C DATA SHEETLRJT 1

INTEGRATED CRUISE

DESCENT CORRECTION

LONG RANGE CRUISE

033-11253 A

DATA SHEETLRJT 1

INTERGRATED CRUISE

033-11253 B

DATA SHEETLRJT 1

INTERGRATED CRUISE

033-11253 C

DATA SHEETLRJT 1

INTEGRATED CRUISE

CLIMB CORRECTION

LONG RANGE SPEED

CLIMB TO OPTIMUM FL

033-11253 D

DATA SHEETLRJT 1

INTEGRATED CRUISE

DESCENT CORRECTION

LONG RANGE CRUISE

033-11254 A

DATA SHEETLRJT 1

INTERGRATED CRUISE

033-11254 B

DATA SHEETLRJT 1

INTERGRATED CRUISE

INTEGRATED CRUISE

CLIMB CORRECTION

LONG RANGE SPEED

CLIMB TO OPTIMUM FL

033-11254 D DATA SHEETLRJT 1

INTEGRATED CRUISE

DESCENT CORRECTION

LONG RANGE CRUISE

033-11255 A

DATA SHEETLRJT 1

INTERGRATED CRUISE

INTEGRATED CRUISE

CLIMB CORRECTION

LONG RANGE SPEED

CLIMB TO OPTIMUM FL

INTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables as follows to take into account the descent down to 1500 feet followed by 6 min IFR approach and landing.

LONG RANGE CRUISE

033-11259 A

DATA SHEETLRJT 1

FUEL TANKING

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310 Planned TOW = 200 000 kg (mission weight without fuel tanking) Air Distance = 2500 NM Enter graph For the given air distance, the optimum fuel tanking weight is 187 000 kg, which is lower than the planned takeoff weight d no fuel tanking recommended.2. fuel price ratio = 0.890Cruising Altitude = FL 350Planned TOW = 190 000 kg (mission weight without fuel tanking) Air Distance = 3250 NM Enter graphFor the given air distance, the optimum fuel tanking weight is 198 000 kg, which is 8 000 kg higher than the planned takeoff weight d optimum quantity of extra fuel is 8 000 kg. Check :a) new TOW less or equal MTOW from departure airport.b) total fuel to be loaded less or equal maximum fuel capacity.c) MLW at destination

033-11260 A

DATA SHEETLRJT 1

FUEL TANKING

033-11261 A

ICAO MODEL FLIGHT PLAN FORM

033-11262 A

033-11270 A

DATA SHEETLRJT 1

033-11271 A

DATA SHEETLRJT 1

INTERGRATED CRUISE

033-11702 A

033-11704 A

033-11717 A

033-12275 A

033-12276 A

033-12277 A

033-12280 A

033-12281 A

033-12285 A

033-12289 A

033-12302 A

DATA SHEET MRJT 1

5.2 Wind Range Correction (Fig. 4.5.2)

This graph is used for conversion of nautical ground miles to nautical air miles. (This is intended for use in conjunction with the 'integrated range' tables). Enter graph with average TAS. Correct for wind component. Move to ground distance at the right then vertically down to read corresponding air distance. For longer distances than shown on the graph apply a factor of 10 to the tabulated values.

Figure 4.5.2 WIND RANGE CORRECTION GRAPH

033-12302 B CIVIL AVIATION AUTHORITY FUEL PLANNING

DATA SHEET MRJT 1

NOTE - OPTIMUM WEIGHT FOR PRESSURE ALTITUDE IS55500 KGTHRUST LIMITED WEIGHT FOR ISA + 10 AND COLDER IS 67100 KG

IS 65700 KG IS 64000 KG

DATA SHEET MRJT 1

NOTE - OPTIMUM WEIGHT FOR PRESSURE ALTITUDE IS55500 KGTHRUST LIMITED WEIGHT FOR ISA + 10 AND COLDER IS 67100 KG

IS 65700 KG IS 64000 KG

033-12304 A

DATA SHEET MRJT 1

033-12305 A

DATA SHEET MRJT 1

033-12306 A

DATA SHEET MRJT 1

033-12306 B

DATA SHEET MRJT 1

Figure 4.5.3.3 Mach 0.78 Cruise All Engines Maximum Cruise Thrust Limits A/C Auto

DATA SHEET MRJT 1

Figure 4.5.3.3 Mach 0.78 Cruise All Engines Maximum Cruise Thrust Limits A/C Auto

DATA SHEET MRJT 1

033-12308 B

DATA SHEET MRJT 1

Figure 4.5.3.4 LOW LEVEL CRUISE 300KIAS All Engines Maximum Cruise Thrust Limits A/C Auto

033-12309 A

DATA SHEET MRJT 1

5.2 Wind Range Correction (Fig. 4.5.2)This graph is used for conversion of nautical ground miles to nautical air miles. (This is intended for use in conjunction with the 'integrated range' tables). Enter graph with average TAS. Correct for wind component. Move to ground distance at the right then vertically down to read corresponding air distance. For longer distances than shown on the graph apply a factor of 10 to the tabulated values.

033-12309 B CIVIL AVIATION AUTHORITYFUEL PLANNING

DATA SHEET MRJT 1

Figure 4.5.3.4 LOW LEVEL CRUISE 300KIAS All Engines Maximum Cruise Thrust Limits A/C Auto

DATA SHEET MRJT 1

Figure 4.4

FLAPS UP

033-12311 A

DATA SHEET MRJT 1

Figure 4.4

FLAPS UP

033-12312 A CIVIL AVIATION AUTHORITY FUEL PLANNING

DATA SHEET MRJT 1

033-12314 A

033-12315 A

033-12316 A

033-12317 A

033-12318 A

033-12319 A

033-12320 A – 033-12328A

033-12329 A - 033-12338 A

033-12339 A

DATA SHEET MRJT 1

Figure 4.3.1 C SIMPLIFIED FLIGHT PLANNING

LONG RANGE CRUISE

033-12340 A

DATA SHEET MRJT 1

3.2 Step Climb Simplified Fuel Planning (Fig. 4.3.5)This chart allows the planner to optimize aeroplane performance by increasing the cruise altitude in 4000 ft. steps in order to allow for the increase in optimum altitude as aeroplane weight decreases.The graph is valid for altitudes with 'Step Climb' of 4000 ft. to 2000 ft above optimum altitude. The graph provides trip fuel and time, at LRC or 0.74M, from brake release to touchdown. The method of use is the same as that for the constant altitude charts except that the argument of 'brake release weight is used in place of cruise 'pressure altitude'- see example on chart

Figure 4.3.5 SIMPLIFIED FLIGHT PLANNING

STEPPED CLIMB CRUISEVALID FOR ALL PRESSURE ALTITUDES WITH 4000 FT STEP CLIMB TO 2000 FT

ABOVE OPTIMUM ALTITUDE

033-12341 A

DATA SHEET MRJT 1

LONG RANGE CRUISE

033-12342 A

DATA SHEET MRJT 1

LONG RANGE CRUISE

DATA SHEET MRJT 1

LONG RANGE CRUISE

033-12345 A

DATA SHEET MRJT 1

LONG RANGE CRUISE

033-12347 A, 033-12348 A CIVIL AVIATION AUTHORITYFUEL PLANNING

DATA SHEET MRJT 1

LONG RANGE CRUISE

033-12350 A, 033-12351 A CIVIL AVIATION AUTHORITYFUEL PLANNING

DATA SHEET MRJT 1

033-12359 A - 033-12361 A

DATA SHEET MRJT 1

Figure 4.7.3 In Flight Diversion (LRC) ONE ENGINE INOPERATIVE

033-12364 A - 033-12366 A CIVIL AVIATION AUTHORITYFUEL PLANNING

DATA SHEET MRJT 1

Figure 4.7.2 Area of Operation - Diversion DistanceONE ENGINE INOPERATIVE

ISABASED ON DRIFTDOWN STARTING AT OR NEAR OPTIMUM ALTITUDE

033-12367 A

DATA SHEET MRJT 1

5.4 DescentThese tables (Fig. 4.5.4) provide tabulations of time, fuel and distance for "flight idle" thrust at 0.74 mach/250 KIAS (economy) and 0.70 Mach/280 KIAS (turbulence penetration)Allowances are made for a straight in approach with gear down. Figure 4.5.4 Descent

.74M/250 KIAS

.70M/280/250 KIAS

BASED ON IDLE THRUST.ALLOWANCES FOR A STRAIGHT-IN APPROACH ARE INCLUDED.

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