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

2. AGENDA Purpose New TOLD cards Example problem
Part I- Back of TOLD card
Part II- Front of TOLD card
Conclusion 4

3. PURPOSE The purpose of this presentation is to provide
guidance and disseminate the changes to the
TOLD card to ensure safe flight planning.
INDIVIDUAL & CREW PROFICIENCY EVALS --
A TOTAL OF 216 PROFICIENCY EVALUATIONS WERE CONDUCTED,
161 WERE SATISFACTORY.
ATP/ATM IMPLEMENTATION --
* IATF DOCUMENTATION-
(GENERAL HOUSECLEANING IS IN ORDER)
* NON-RATED CREWMEMBER PROGRAM
(FIs & SIs NEED ENHANCED TNG IN INSTRUCTOR FUNDAMENTALS DURING
RL PROGRESSION).
* SIMULATED ENGINE FAILURE TRAINING --
(RECOMMEND UNITS CONTINUE TO EMPHASIS SIMULATED ENG FAILURE TNG)
***COMMENDABLES : CW2 KURZ (15TH MI BN) -- EXCEPTIONAL ENGINE CLASS
15TH MI BN STANS PERSONNEL -- EXCEPTIONAL UAV CLASS
2-227TH STANS PERSONNEL -- EXCEPTIONAL IATFs
FLIGHT OPS/FLIGHT PLANNING -- MISSION BRIEFING PROCEEDURES NEED TO BE
UPDATED TO REFLECT THE REQUIREMENTS FOR PIN FILTER (HIRTA MESSAGE)
REMOVAL.
NIGHT VISION DEVICES --
* MAINTAINER / USER CONTINUATION TRAINING - MAINTAINERS MUST RECEIVE
CURRENT TRAINING IN CORRECT UP TO DATE MAINTENANCE PROCEDURES
TO ENABLE PROPER MAINTENANCE OF NVDs. USERS MUST RECIEVE APPROPRIATE
TRAINING DURING READINESS LEVEL PROGRESSION TO ENSURE SAFE/EFFICIENT
CONTINUATION TNG. 12

4. REFERENCES TM
TC 1-218, Task # 1022

5. NEW TOLD CARD

6. EXAMPLE MISSION:
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 subtotal: lbs.
Baggage and equipment- 6 bags, 1box subtotal: lbs.
Total load: lbs. 14

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, 500-2
or STAN w/ MIN CLIMB 250/NM to 5000’
INDIVIDUAL & CREW PROFICIENCY EVALS --
A TOTAL OF 216 PROFICIENCY EVALUATIONS WERE CONDUCTED,
161 WERE SATISFACTORY.
ATP/ATM IMPLEMENTATION --
* IATF DOCUMENTATION-
(GENERAL HOUSECLEANING IS IN ORDER)
* NON-RATED CREWMEMBER PROGRAM
(FIs & SIs NEED ENHANCED TNG IN INSTRUCTOR FUNDAMENTALS DURING
RL PROGRESSION).
* SIMULATED ENGINE FAILURE TRAINING --
(RECOMMEND UNITS CONTINUE TO EMPHASIS SIMULATED ENG FAILURE TNG)
***COMMENDABLES : CW2 KURZ (15TH MI BN) -- EXCEPTIONAL ENGINE CLASS
15TH MI BN STANS PERSONNEL -- EXCEPTIONAL UAV CLASS
2-227TH STANS PERSONNEL -- EXCEPTIONAL IATFs
FLIGHT OPS/FLIGHT PLANNING -- MISSION BRIEFING PROCEEDURES NEED TO BE
UPDATED TO REFLECT THE REQUIREMENTS FOR PIN FILTER (HIRTA MESSAGE)
REMOVAL.
NIGHT VISION DEVICES --
* MAINTAINER / USER CONTINUATION TRAINING - MAINTAINERS MUST RECEIVE
CURRENT TRAINING IN CORRECT UP TO DATE MAINTENANCE PROCEDURES
TO ENABLE PROPER MAINTENANCE OF NVDs. USERS MUST RECIEVE APPROPRIATE
TRAINING DURING READINESS LEVEL PROGRESSION TO ENSURE SAFE/EFFICIENT
CONTINUATION TNG. 3

8. PERFORMANCE PLANNING (Back of TOLD)
Complete the information for the departure airfield as follows:
Field Length Available -
Temperature -
Pressure Altitude -
6000 30
4000 13

9. 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
6000 30
4000 13

10. 14,000

11. 12,750

12. 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
6000 30
4000
14000
12750 13

13. 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
6000 30
4000
14000
12750 13

14. Baseline
12,800

15. Baseline
14,000

16. 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
6000 30
4000
14000
12750
12800
14000 13

17. 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.
6000 30
4000
14000
12750
12800
14000 13

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.

19. 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%
6000 30
4000
14000
12750
12800
14000
Insert the 4.1% into Figure 7A-31 to determine the Max Wt to achieve a 4.1 SE Grad Climb.
4.1 13

20. Baseline
12,600

21. 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
6000 30
4000
14000
12750
12800
14000
12600
4.1 13

22. 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.
6000 30
4000
14000
12750
12800
14000
12600
12600
4.1 13

23. CONFIGURATION 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.

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.

25. THE FRONT OF THE TOLD CARD
PART II
THE FRONT OF THE TOLD CARD

26. PERFORMANCE PLANNING (Front of TOLD)
Complete the information for the departure airfield as follows:
Station
Field Length Available
Temperature
Pressure Altitude
Takeoff Weight (determined from back of card)
AAA
6000
+30
4000
12600

27. 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
6000
+30
4000
12600

28. 90%

29. 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
6000
+30
4000
12600
90%

30. 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
6000
+30
4000
12600
90% X

31. 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
6000
+30
4000
12600
90% X

32. 5900
12,600

33. 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
6000
+30
4000
12600
90% X
5900

34. 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
6000
+30
4000
12600
90% X
5900

35. 8,800

36. 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
6000
+30
4000
12600
90% X
5900
8800

37. PERFORMANCE PLANNING (Front of TOLD)
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

38. 112

39. PERFORMANCE PLANNING (Front of TOLD)
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
112

40. PERFORMANCE PLANNING (Front of TOLD)
Determine the V2 / Vyse Speed
use Figure 7A-31 Climb - One Engine Inoperative
AAA
6000
+30
4000
12600
90% X
5900
8800
112

41. 122

42. PERFORMANCE PLANNING (Front of TOLD)
Determine the V2 / Vyse Speed
use Figure 7A-31 Climb - One Engine Inoperative
AAA
6000
+30
4000
12600
90% X
5900
8800
112
122

43. PERFORMANCE PLANNING (Front of TOLD)
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
8800
112
122
106

44. PERFORMANCE PLANNING (Front of TOLD)
Climb Gradient Alt -
the altitude as specified for SE Climb Grad in the Departure Procedure.
AAA
6000
+30
4000
12600
90% X
5900
8800
112
122
106
5000

45. 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
6000
+30
4000
12600
90% X
5900
8800
112
122
106
5000

46. PERFORMANCE PLANNING (Front of TOLD)
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
8800
112
122
106
5000
6000
12600

47. PERFORMANCE PLANNING (Front of TOLD)
Compute the Vref speed
Vref = 1.3 times landing weight
use Figure 7A-13, Stall Speeds - Power Idle to determine Vso.
AAA
6000
+30
4000
12600
90% X
5900
8800
112
122
106
5000
6000
12600

48. 75 knots

49. PERFORMANCE PLANNING (Front of TOLD)
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
8800
112
122
106
5000
6000
12600 98

50. PERFORMANCE PLANNING (Front of TOLD)
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
8800
112
122
106
5000
6000
12600 98

51. PERFORMANCE PLANNING (Front of TOLD)
Compute the Vapp Speed:
For a normal instrument approach, Vapp is Vref plus 20
For a stabilized approach, Vapp is Vref plus 10
For 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
8800
112
122
106
5000
6000
12600 98
118

52. PERFORMANCE PLANNING (Front of TOLD)
Determine the Landing Distance
use Figure 7A-107, Normal Landing Distance Without Propeller Reversing, Flaps DOWN
AAA
6000
+30
4000
12600
90% X
5900
8800
112
122
106
5000
6000
12600 98
118

53. 2,000 ft

54. PERFORMANCE PLANNING (Front of TOLD)
Determine the Landing Distance
use Figure 7A-107, Normal Landing Distance Without Propeller Reversing, Flaps DOWN
AAA
6000
+30
4000
12600
90% X
5900
8800
112
122
106
5000
6000
12600 98
118
2000

55. CONCLUSION