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

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2 AGENDAAGENDA 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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3 PURPOSEPURPOSE 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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4 REFERENCESREFERENCES 1.TM TC 1-218, Task # 1022

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NEW TOLD CARD

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6 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: 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: lbs. Total load: 1325 lbs. EXAMPLE MISSION:

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7 CONDITIONS (AAA) OAT: +30°C(85 °F) FLD ELE: 3800 ft ALT SET: 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, or STAN w/ MIN CLIMB 250/NM to 5000 OAT: +30°C(85 °F) FLD ELE: 3800 ft ALT SET: 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, or STAN w/ MIN CLIMB 250/NM to 5000

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PERFORMANCE PLANNING (Back of TOLD) Complete the information for the departure airfield as follows: (1)Field Length Available - (2)Temperature - (3)Pressure Altitude

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PERFORMANCE PLANNING (Back of TOLD) Determine the maximum weight to achieve single engine climb use Figure 7A-15 for Flaps UP and Figure 7A-16 for Flaps APPROACH

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14,000

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12,750

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PERFORMANCE PLANNING (Back of TOLD) Determine the maximum weight to achieve single engine climb use Figure 7A-15 for Flaps UP and Figure 7A-16 for Flaps APPROACH

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PERFORMANCE PLANNING (Back of TOLD) Determine the maximum weight for ACC/STOP - use Figure 7A-22, Accelerate – Stop, Flaps UP and Figure 7A-26, Accelerate – Stop Flaps APPROACH

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Baseline 12,800

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14,000 Baseline

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PERFORMANCE PLANNING (Back of TOLD) Determine the maximum weight for ACC/STOP - use Figure 7A-22, Accelerate – Stop, Flaps UP and Figure 7A-26, Accelerate – Stop Flaps APPROACH

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PERFORMANCE PLANNING (Back of TOLD) 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

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18 Max Wt For Required SE CLB 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.

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PERFORMANCE PLANNING (Back of TOLD) Use the formula on the bottom of the TOLD card to compute climb gradient in percent. (250 ft/nm 6076) 100 = 4.1% Insert the 4.1% into Figure 7A-31 to determine the Max Wt to achieve a 4.1 SE Grad Climb.

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12,600 Baseline

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PERFORMANCE PLANNING (Back of TOLD) Enter the value derived for the Maximum Weight for Required SE CLB GRAD - use Figure 7A-31, Climb – One Engine Inoperative

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PERFORMANCE PLANNING (Back of TOLD) 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

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23 CONFIGURATIONCONFIGURATION 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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24 ZERO 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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25 PART II THE FRONT OF THE TOLD CARD

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PERFORMANCE PLANNING (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

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PERFORMANCE PLANNING (Front of TOLD) 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

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90%

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PERFORMANCE PLANNING (Front of TOLD) 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 %

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PERFORMANCE PLANNING (Front of TOLD) Determine the Configuration Based on the back of the TOLD card, the maximum takeoff weight of lbs. allows for a flaps up takeoff. Place an X in the Flaps 0% block. AAA % X

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PERFORMANCE PLANNING (Front of TOLD) 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 % X

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12,

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PERFORMANCE PLANNING (Front of TOLD) 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 % X 5900

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PERFORMANCE PLANNING (Front of TOLD) Determine the Accelerate / Go Distance Use Figure 7A-23 Accelerate – Go, Flaps Up or Figure 7A-27 Accelerate – Go, Flaps APPROACH AAA % X 5900

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8,800

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PERFORMANCE PLANNING (Front of TOLD) 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 % X

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PERFORMANCE PLANNING (Front of TOLD) Determine the V 1 / V R Speed - use Figure 7A-21 Takeoff Distance, Flaps UP or Figure 7A-25 Takeoff Distance, Flaps APPROACH AAA % X

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112

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PERFORMANCE PLANNING (Front of TOLD) Determine the V 1 / V R Speed - use Figure 7A-21 Takeoff Distance, Flaps UP or Figure 7A-25 Takeoff Distance, Flaps APPROACH AAA % X

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PERFORMANCE PLANNING (Front of TOLD) Determine the V 2 / V yse Speed use Figure 7A-31 Climb - One Engine Inoperative AAA % X

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122

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PERFORMANCE PLANNING (Front of TOLD) Determine the V 2 / V yse Speed use Figure 7A-31 Climb - One Engine Inoperative AAA % X

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PERFORMANCE PLANNING (Front of TOLD) Determine the V x Speed Obtain the V x speed from the Takeoff Distance, Flaps APPROACH chart, FIG 7A- 25, Tabular Data at the top of the page, column labeled V x. AAA % X

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PERFORMANCE PLANNING (Front of TOLD) Climb Gradient Alt - the altitude as specified for SE Climb Grad in the Departure Procedure. AAA % X

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PERFORMANCE PLANNING (Front of TOLD) 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 % X

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PERFORMANCE PLANNING (Front of TOLD) Enter the Landing Data information Enter the runway length available and the landing weight based on takeoff conditions. AAA % X

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PERFORMANCE PLANNING (Front of TOLD) Compute the V ref speed V ref = 1.3 times V landing weight u se Figure 7A-13, Stall Speeds - Power Idle to determine V so. AAA % X

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75 knots

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PERFORMANCE PLANNING (Front of TOLD) Complete as follows: V so is 75 knots V ref = 75 x 1.3 V ref = 98 knots (97.5 rounded up to 98) AAA % X

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PERFORMANCE PLANNING (Front of TOLD) There is another method to determine V ref. 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 % X

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PERFORMANCE PLANNING (Front of TOLD) Compute the V app Speed: For a normal instrument approach, V app is V ref plus 20 For a stabilized approach, V app is V ref plus 10 For a visual approach, V app is between V ref and V ref plus 10 as determined by the PC In this case a normal instrument approach is planned. AAA % X

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PERFORMANCE PLANNING (Front of TOLD) Determine the Landing Distance use Figure 7A-107, Normal Landing Distance Without Propeller Reversing, Flaps DOWN AAA % X

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2,000 ft

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PERFORMANCE PLANNING (Front of TOLD) Determine the Landing Distance use Figure 7A-107, Normal Landing Distance Without Propeller Reversing, Flaps DOWN AAA % X

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CONCLUSIONCONCLUSION

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