FLIGHT THEORY

ATPL(A) ANNEXES 033Rev. w

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033-9558 AENDURANCE/FUEL CALCULATION

Fuel (kg) Time (hh:mm)

Trip FuelContingency FuelAlternate FuelFinal Reserve Fuel

5800

18001325

02:32

00:42

Minimum T/O-FuelExtra Fuel

Actual T/O-FuelTaxi FUEL 200

Ramp Fuel 10000

033-11073 B

DATA SHEETLRJT 1

FLIGHT PLANNINGGROUND DISTANCE/AIR DISTANCE

SEQ A

033-11073 CDATA SHEETLRJT 1

FLIGHT PLANNINGQUICK DERTERMINATION OF F-PLN SEQ A

033-11073 D

DATA SHEETLRJT 1

FLIGHT PLANNINGQUICK DERTERMINATION OF F-PLN SEQ A

033-11074 AJAR - FCL FLIGHT PLANNING

QUICK DETERMINATION OF FLIGHT PLAN

INTRODUCTION

The following flight planning tables allow the planner to determine trip fuel consumption and trip timerequired 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 OFF

Note: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 referencelanding weightIf it is lover (or greater) man the reference landing weight subtract (or add) the value given in thecorrection part of the table per 1000 kg below (or above) the reference landing weight.

033-11074 BDATA SHEETLRJT 1

FLIGHT PLANNINGGROUND DISTANCE/AIR DISTANCE SEQ A

033-11074 CDATA SHEETLRJT 1

FLIGHT PLANNINGQUICK DERTERMINATION OF F-PLN SEQ A

033-11074 D

DATA SHEETLRJT 1

FLIGHT PLANNINGQUICK DERTERMINATION OF F-PLN SEQ A

033-11181 – 82 – 83 – 84 – 85 – 86 – 87 – 88 - 89 A

033-11190-91-92-93-94 A

033-11195-96-97-98 A

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

TAF EDDK ISSUED AT 042200EDDK 0624 14005KT 7000 NSCBECMG 0608 CAVOKTEMPO 1115 9999 SCT040 =

TAF EDDL ISSUED AT 042200EDDL 0624 16003KT 5000 NSCBECMG 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 EGLL ISSUED AT 042200EGLL 0624 17005KT 5000 SCT040PROB30 TEMPO 0607 1500 BRBECMG 0811 23010KT 9999BECMG 1619 BRNO15 =

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

JAR - FCL FLIGHT PLANNINGQUICK DETERMINATION OF FLIGHT PLAN

INTRODUCTION

The following flight planning tables allow the planner to determine trip fuel consumption and trip timerequired 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 thecorresponding FL.

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

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

CORRECTION FOR DEVIATION FROM REFERENCE LANDING WEIGHT

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

033-11204 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGGROUND DISTANCE/AIR DISTANCE

LONG RANGE CRUISE ABOVE FL250

033-11204 C

JAR - FCL FLIGHT PLANNINGGROUND DISTANCE/AIR DISTANCE

033-11207 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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 atdestination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking)Air Distance = 2500 NMEnter 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 NMEnter 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

033-11207 B

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11208 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11209 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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 atdestination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking)Air Distance = 2500 NMEnter graphFor 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 350Planned TOW = 190 000 kg (mission weight without fuel tanking)Air Distance = 3250 NMEnter 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 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 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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/250kt

Note: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 NMEnter graphFor the given air distance, the optimum fuel tanking weight is 187 000 kg, which is lower than theplanned 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 NMEnter graphFor the given air distance, the optimum fuel tanking weight is 198 000 kg, which is 8 000 kg higher thanthe 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

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11211 A

JAR - FCL FLIGHT PLANNINGQUICK DETERMINATION OF FLIGHT PLAN

INTRODUCTION

The following flight planning tables allow the planner to determine trip fuel consumption and trip timerequired 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 thecorresponding FL.

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

3. For each degree Celsius above ISA temperature apply fuel correction 0.010 (kg/°C/NM) xISA(°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 referencelanding weightIf it is lover (or greater) man the reference landing weight subtract (or add) the value given in thecorrection part of the table per 1000 kg below (or above) the reference landing weight.

033-11211 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGQUICK DERTERMINATION OF F-PLN

033-11212 A

JAR - FCL FLIGHT PLANNINGQUICK DETERMINATION OF FLIGHT PLAN

INTRODUCTION

The following flight planning tables allow the planner to determine trip fuel consumption and trip timerequired 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 thecorresponding FL.

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

3. For each degree Celsius above ISA temperature apply fuel correction 0.010 (kg/°C/NM) xISA(°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 referencelanding weightIf it is lover (or greater) man the reference landing weight subtract (or add) the value given in thecorrection part of the table per 1000 kg below (or above) the reference landing weight.

033-11212 B

JAR - FCL FLIGHT PLANNINGQUICK DERTERMINATION OF F-PLN

033-11213 A

JAR - FCL FLIGHT PLANNINGQUICK DETERMINATION OF FLIGHT PLAN

INTRODUCTION

The following flight planning tables allow the planner to determine trip fuel consumption and trip timerequired 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 thecorresponding FL.

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

3. For each degree Celsius above ISA temperature apply fuel correction 0.010 (kg/°C/NM) xISA(°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 referencelanding weightIf it is lover (or greater) man the reference landing weight subtract (or add) the value given in thecorrection part of the table per 1000 kg below (or above) the reference landing weight.

033-11213 B

JAR - FCL FLIGHT PLANNINGQUICK DERTERMINATION OF F-PLN

033-11214 A

JAR - FCL FLIGHT PLANNINGQUICK DETERMINATION OF FLIGHT PLAN

INTRODUCTION

The following flight planning tables allow the planner to determine trip fuel consumption and trip timerequired 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:

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

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

6. For each degree Celsius above ISA temperature apply fuel correction 0.010 (kg/°C/NM) xISA(°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 referencelanding weightIf it is lover (or greater) man the reference landing weight subtract (or add) the value given in thecorrection part of the table per 1000 kg below (or above) the reference landing weight.

033-11214 BJAR - FCL FLIGHT PLANNING

QUICK DERTERMINATION OF F-PLN

033-11215 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

033-11216 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

033-11223 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

033-11223 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11223 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11223 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11223 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables as follows to take intoaccount 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

033-11223 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables as follows to take intoaccount 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

033-11223 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables as follows to take intoaccount 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 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

033-11224 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11224 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11224 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11224 C

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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 C

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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 C

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11226 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLACRUISE LEVEL

033-11226 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLCRUISE LEVEL

033-11228 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGGROUND DISTANCE/AIR DISTANCE

LONG RANGE CRUISE ABOVE FL250

033-11229 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLACRUISE LEVEL

033-11231 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGGROUND DISTANCE/AIR DISTANCE

LONG RANGE CRUISE ABOVE FL250

033-11238 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11239 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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 atdestination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking)Air Distance = 2500 NMEnter 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 NMEnter 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

033-11239 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11240 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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:

3. ff necessary, step climbs are performed to reach the indicated flight levels.4. 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 atdestination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking)Air Distance = 2500 NMEnter 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 NMEnter 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

033-11240 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11241 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11243 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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:

5. ff necessary, step climbs are performed to reach the indicated flight levels.6. 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 atdestination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking)Air Distance = 2500 NMEnter 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 NMEnter 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

033-11243 B

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11244 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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:

7. ff necessary, step climbs are performed to reach the indicated flight levels.8. 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 atdestination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking)Air Distance = 2500 NMEnter 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 NMEnter 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

033-11244 B

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11245 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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:

9. ff necessary, step climbs are performed to reach the indicated flight levels.10. 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 atdestination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking)Air Distance = 2500 NMEnter 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 NMEnter 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

033-11245 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11252 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11252 B

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11252 B

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11252 B

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11252 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11252 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11252 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11253 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11253 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11253 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11253 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11253 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11253 DDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11253 DDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11253 DDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11254 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11254 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11254 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11254 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11254 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11254 DDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11254 DDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11254 DDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables äs follows to take intoaccount 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

033-11255 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11255 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11255 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11255 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

CLIMB CORRECTION

The planner must correct the values for the fuel and the time obtained from the integrated cruise tableswith the numbers given in the following tables. The tables which are established for M.80, M.82, M.84and 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 acorrection of 160 kg per step climb to the fuel consumption.

033-11255 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables as follows to take intoaccount 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

033-11255 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables as follows to take intoaccount 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

033-11255 CDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTEGRATED CRUISE

DESCENT CORRECTION

Correct the fuel and the time values determined in the integrated cruise tables as follows to take intoaccount 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

033-11259 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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 atdestination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking)Air Distance = 2500 NMEnter 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 NMEnter graphFor the given air distance, the optimum fuel tanking weight is 198 000 kg, which is 8 000 kg higher thanthe 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

033-11259 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11260 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

FUEL TANKING

GENERALFuel tanking graphs allow to determine the Optimum fuel quantity to be tanked as a function of the fuelprice ratio between departure and destination airports. The following pages present for one flight levelper page the Optimum aircraft takeoff weight depending on the fuel price ratio (departure fuel pricedivided 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 thetransport of the extra (tanked) fuel and it is the weight at which the maximum profit can be achieved. Thequantity of extra fuel that can be loaded is calculated as the difference between the Optimum takeoffweight (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 atdestination).

EXAMPLES1. Fuel price ratio = 0.930Cruising Altitude = FL310Planned TOW = 200 000 kg (mission weight without fuel tanking)Air Distance = 2500 NMEnter 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 NMEnter 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 BDATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGFUEL TANKING

033-11261 A

033-11270 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGICAO MODEL FLIGHT PLAN FORM

033-11271 A

DATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11272 ADATA SHEETLRJT 1

JAR - FCL FLIGHT PLANNINGINTERGRATED CRUISE

033-11702 A

033-11704 A

033-11717 A

033-11702 A

033-11704 A

033-11717 A

033-11702 A

033-11704 A

033-11717 A

033-12314 - 12319A

033-12320 A a 033-12328A

033-12329 A - 033-12338 A