1 TAKEOFF AND LANDING DATA (TOLD) CARDS FOR C12 D2/T1/T2.

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TAKEOFF AND LANDING DATA (TOLD) CARDS FOR C12 D2/T1/T2

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AGENDAAGENDAAGENDAAGENDA

• Purpose

• New TOLD cards

• Example problem

• Part I- Back of TOLD card

• Part II- Front of TOLD card

• Conclusion

• Purpose

• New TOLD cards

• Example problem

• Part I- Back of TOLD card

• Part II- Front of TOLD card

• Conclusion

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PURPOSEPURPOSEPURPOSEPURPOSE

The purpose of this presentation is to provide guidance and disseminate the changes to the

TOLD card to ensure safe flight planning.

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REFERENCESREFERENCESREFERENCESREFERENCES

1. TM 1-1510-218-10

2. TC 1-218, Task # 1022

NEW TOLD CARDNEW TOLD CARDNEW TOLD CARDNEW TOLD CARD

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Mission: Transport the following load (personnel, baggage and equipment) from Airport Alpha (AAA) to Airport Bravo (BBB), a distance of 700 NM with a cruising altitude of FL240. Personnel - 6 subtotal: 1060 lbs. Baggage and equipment- 6 bags, 1box subtotal: + 265 lbs.

Total load: 1325 lbs.

Mission: Transport the following load (personnel, baggage and equipment) from Airport Alpha (AAA) to Airport Bravo (BBB), a distance of 700 NM with a cruising altitude of FL240. Personnel - 6 subtotal: 1060 lbs. Baggage and equipment- 6 bags, 1box subtotal: + 265 lbs.

Total load: 1325 lbs.

EXAMPLE MISSION:EXAMPLE MISSION:EXAMPLE MISSION:EXAMPLE MISSION:

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CONDITIONS (AAA)CONDITIONS (AAA)CONDITIONS (AAA)CONDITIONS (AAA)

OAT: +30°C(85 °F)

FLD ELE: 3800 ft

ALT SET: 29.72 in. Hg

PRESSURE ALTITUDE: 4000 ft

WIND: 330 ° at 10 kts

RWY 35 : 6000 ft

WEATHER: 400 ft OVC

VIS: 1 M, RA/HA

NON-STAN T/O MIN: RWY 35, 500-2 or STAN w/ MIN CLIMB 250/NM to 5000’

OAT: +30°C(85 °F)

FLD ELE: 3800 ft

ALT SET: 29.72 in. Hg

PRESSURE ALTITUDE: 4000 ft

WIND: 330 ° at 10 kts

RWY 35 : 6000 ft

WEATHER: 400 ft OVC

VIS: 1 M, RA/HA

NON-STAN T/O MIN: RWY 35, 500-2 or STAN w/ MIN CLIMB 250/NM to 5000’

PERFORMANCE PLANNING PERFORMANCE PLANNING (Back of TOLD)(Back of TOLD)


Complete the information for the departure airfield as follows:

(1) Field Length Available -

(2) Temperature -

(3) Pressure Altitude -

600030 4000



Determine the maximum weight to achieve single engine climb

use Figure 7A-15 for Flaps UP

and Figure 7A-16 for Flaps

APPROACH

600030 4000

14,000

12,750



Determine the maximum weight to achieve single engine climb

use Figure 7A-15 for Flaps UP

and Figure 7A-16 for Flaps

APPROACH

600030 4000

14000 12750



Determine the maximum weight for ACC/STOP -

use Figure 7A-22, Accelerate – Stop, Flaps UP

and Figure 7A-26, Accelerate – Stop Flaps APPROACH

600030 4000

14000 12750

Baseline

12,800

14,000

Baseline



Determine the maximum weight for ACC/STOP -

use Figure 7A-22, Accelerate – Stop, Flaps UP

and Figure 7A-26, Accelerate – Stop Flaps APPROACH

600030 4000

14000 12750

12800 14000



Determine the Maximum Weight for Required SE CLB GRAD -

use Figure 7A-31, Climb – One Engine Inoperative

Before beginning, determine if standard or non-standard takeoff minimums apply.

600030 4000

14000 12750

12800 14000

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Max Wt For Required SE Max Wt For Required SE CLB GRADCLB GRAD

Max Wt For Required SE Max Wt For Required SE CLB GRADCLB GRAD

• A 3.3% SE climb gradient required for all IFR takeoffs.

• Weather does not meet Non-standard T.O. minimums.• SE Climb Gradient of 250 ft/nm must now be met.• Therefore 250 ft/nm must be converted to a 4.1% climb

gradient using the formula on the bottom of the TOLD card.

• A 3.3% SE climb gradient required for all IFR takeoffs.

• Weather does not meet Non-standard T.O. minimums.• SE Climb Gradient of 250 ft/nm must now be met.• Therefore 250 ft/nm must be converted to a 4.1% climb

gradient using the formula on the bottom of the TOLD card.



Use the formula on the bottom of the TOLD card to compute climb gradient in percent.

(250 ft/nm 6076) 100 = 4.1%

600030 4000

14000 12750

12800 14000

4.1

Insert the 4.1% into Figure 7A-31 to determine the Max Wt to achieve a 4.1 SE Grad Climb.

Insert the 4.1% into Figure 7A-31 to determine the Max Wt to achieve a 4.1 SE Grad Climb.

12,600

Baseline



Enter the value derived for the Maximum Weight for Required SE CLB GRAD -

use Figure 7A-31, Climb – One Engine Inoperative

600030 4000

14000 12750

12800 14000

4.1

12600



Determine the Maximum Allowable Takeoff Weight based on the most restrictive condition.

In this case, the most restricted aircraft weight condition is based on the value derived from the climb gradient. Enter this value.

600030 4000

14000 12750

12800 14000

4.1

12600

12600

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CONFIGURATIONCONFIGURATIONCONFIGURATIONCONFIGURATION

• With the backside completed, the crew can decide

upon the configuration.

• The decision is based on which configuration has the

most restrictive max allowable takeoff weight.

• In this example, the max allowable takeoff weight is 12, 600 lbs.

• This will allow a takeoff with flaps UP, because max weight with flaps up is 12,800 lbs.

• With the backside completed, the crew can decide

upon the configuration.

• The decision is based on which configuration has the

most restrictive max allowable takeoff weight.

• In this example, the max allowable takeoff weight is 12, 600 lbs.

• This will allow a takeoff with flaps UP, because max weight with flaps up is 12,800 lbs.

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ZERO FUEL WEIGHTZERO FUEL WEIGHTZERO FUEL WEIGHTZERO FUEL WEIGHT

• At this point we can determine Zero Fuel Weight.

• In this example the Operating Weight is 9,300 pounds and the Load for the mission is 1,325 pounds.

• Therefore, the the Zero Fuel Weight is 10,625 pounds.

• The takeoff weight of 12,600 minus zero fuel weight

of 10,625 allows for 1,975 pounds for fuel.

• At this point we can determine Zero Fuel Weight.

• In this example the Operating Weight is 9,300 pounds and the Load for the mission is 1,325 pounds.

• Therefore, the the Zero Fuel Weight is 10,625 pounds.

• The takeoff weight of 12,600 minus zero fuel weight

of 10,625 allows for 1,975 pounds for fuel.

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PART IIPART II

THE FRONT OF THE TOLD CARD

THE FRONT OF THE TOLD CARD

PERFORMANCE PLANNING PERFORMANCE PLANNING (Front of TOLD)(Front of TOLD)


Complete the information for the departure airfield as follows:

(1) Station

(2) Field Length Available

(3) Temperature

(4) Pressure Altitude

(5) Takeoff Weight (determined from back of card)

AAA 6000+30 4000

12600



Determine the Minimum Takeoff Power

Use Figure 7A-17 Minimum Takeoff Power at 2000 RPM with Ice Vanes Retracted (65 knots)

or Figure 7A-18 Minimum Takeoff Power with Ice Vanes Extended (65 knots)

AAA 6000+30 4000

12600



Determine the Minimum Takeoff Power

Use Figure 7A-17 Minimum Takeoff Power at 2000 RPM with Ice Vanes Retracted (65 knots)

or Figure 7A-18 Minimum Takeoff Power with Ice Vanes Extended (65 knots)

AAA 6000+30 4000

12600 90%



Determine the Configuration

Based on the back of the TOLD card, the maximum takeoff weight of 12600 lbs. allows for a flaps up takeoff.

Place an X in the Flaps 0% block.

AAA 6000+30 4000

12600 90%X



Determine the T.O. FLD. Length Required -

the actual ACC/STOP distance for a 12,600 pound aircraft.

Use fig. 7A-22, Accelerate – Stop, Flaps UP

AAA 6000+30 4000

12600 90%X

12,600

5900



Determine the T.O. FLD. Length Required -

The actual ACC/STOP distancefor a 12,600 pound aircraft.

Use fig. 7A-22, Accelerate – Stop, Flaps UP

AAA 6000+30 4000

12600 90%X

5900



Determine the Accelerate / Go Distance

Use Figure 7A-23 Accelerate – Go, Flaps Up

or Figure 7A-27 Accelerate –

Go, Flaps APPROACH

AAA 6000+30 4000

12600 90%X

5900



Determine the Accelerate / Go Distance

Use Figure 7A-23 Accelerate – Go, Flaps Up

or Figure 7A-27 Accelerate –

Go, Flaps APPROACH

The Accelerate-Go Distance is advisory only in nature.

AAA 6000+30 4000

12600 90%X

5900 8800



Determine the V1 / VR Speed -

use Figure 7A-21 Takeoff Distance, Flaps UP or Figure 7A-25 Takeoff Distance, Flaps APPROACH

AAA 6000+30 4000

12600 90%X

5900 8800



Determine the V1 / VR Speed -

use Figure 7A-21 Takeoff Distance, Flaps UP or Figure 7A-25 Takeoff Distance, Flaps APPROACH

AAA 6000+30 4000

12600 90%X

5900 8800112



Determine the V2 / Vyse Speed

use Figure 7A-31 Climb - One Engine Inoperative

AAA 6000+30 4000

12600 90%X

5900 8800112



Determine the V2 / Vyse Speed

use Figure 7A-31 Climb - One Engine Inoperative

AAA 6000+30 4000

12600 90%X

5900 8800112 122



Determine the Vx Speed

Obtain the Vx speed from the Takeoff Distance, Flaps APPROACH chart, FIG 7A-25, Tabular Data at the top of the page, column labeled Vx.

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106



Climb Gradient Alt -

the altitude as specified for SE Climb Grad in the Departure Procedure.

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106

5000



Enter the Landing Data information

The landing data is initially calculated at takeoff weight as a contingency for a necessary return to the departure airport right after takeoff. The items must be recalculated for the arrival at the destination.

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106

5000



Enter the Landing Data information

Enter the runway length available and the landing weight based on takeoff conditions.

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106

5000

600012600



Compute the Vref speed

Vref = 1.3 times Vso @ landing weight

use Figure 7A-13, Stall Speeds - Power Idle to determine Vso.

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106

5000

600012600

75 knots



Complete as follows:

Vso is 75 knots

Vref = 75 x 1.3

Vref = 98 knots (97.5 rounded up to 98)

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106

5000

600012600

98



There is another method to determine Vref. Subtract 5 knots from the value obtained from the APPROACH SPEED – KNOTS data table at the top of Fig. 7A-107, Landing Distance Without Propeller Reversing, Flaps DOWN. For a 12,600 pound aircraft the given APPROACH SPEED is 103 KIAS – 5 KIAS = 98 KIAS.

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106

5000

600012600

98



Compute the Vapp Speed:

For a normal instrument approach, Vapp is Vref plus 20 For a stabilized approach, Vapp is Vref plus 10For a visual approach, Vapp is between Vref and Vref plus 10 as determined by the PC

In this case a normal instrument approach is planned.

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106

5000

600012600

98 118



Determine the Landing Distance

use Figure 7A-107, Normal Landing Distance Without Propeller Reversing, Flaps DOWN

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106

5000

600012600

98 118

2,000 ft



Determine the Landing Distance

use Figure 7A-107, Normal Landing Distance Without Propeller Reversing, Flaps DOWN

AAA 6000+30 4000

12600 90%X

5900 8800112 122 106

5000

600012600

98 118

2000

CONCLUSIONCONCLUSIONCONCLUSIONCONCLUSION

1 TAKEOFF AND LANDING DATA (TOLD) CARDS FOR C12 D2/T1/T2.

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Transcript of 1 TAKEOFF AND LANDING DATA (TOLD) CARDS FOR C12 D2/T1/T2.