Command Brief

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

3
PURPOSE

The purpose of this presentation is to provide
guidance and disseminate the changes to the
TOLD card to ensure safe flight planning.
4
REFERENCES

1. TM 1-1510-218-10
2. 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 - 6
subtotal 1060 lbs. Baggage and
equipment- 6 bags, 1box subtotal 265
lbs. Total load 1325 lbs.
7
CONDITIONS (AAA)
OAT 30C(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

8
PERFORMANCE PLANNING (Back of TOLD)

• Complete the information for the departure
  airfield as follows
• Field Length Available -
• Temperature -
• Pressure Altitude -

6000
30
4000

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

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
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
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
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
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
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
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
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
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
12600 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
106
112
122
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
106
112
122
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
106
112
122
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
106
112
122
5000
6000
12600
47
PERFORMANCE PLANNING (Front of TOLD)
Compute the Vref speed Vref 1.3 times Vso _at_
landing weight use Figure 7A-13, Stall Speeds
- Power Idle to determine Vso.
AAA
6000
30
4000
12600
90
X
5900
8800
106
112
122
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
106
112
122
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
106
112
122
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
106
112
122
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
106
112
122
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
106
112
122
5000
6000
12600
98
118
2000
55
CONCLUSION