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

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

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

REFERENCES TM 1-1510-218-10 TC 1-218, Task # 1022

NEW TOLD CARD

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. 14

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’ 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

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

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

14,000

12,750

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 13

Baseline 12,800

Baseline 14,000

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

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

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.

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

Baseline 12,600

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

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

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.

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.

THE FRONT OF THE TOLD CARD PART II THE FRONT OF THE TOLD CARD

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

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%

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%

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

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 12,600

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

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

8,800

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

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

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

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

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

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

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

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

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

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

75 knots

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

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

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

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

2,000 ft

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

CONCLUSION