F16C/D. FLIGHT MANUAL (2002) - page 38

 

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F16C/D. FLIGHT MANUAL (2002) - page 38

 

 

T.O. GR1F16CJ1CL2

P13/PW/CFT

Refusal Speed With Drag Chute

GR1F-16CJ-1CL-1-2013X37

DRAG CHUTE DEPLOYED

DATA BASIS ESTIMATED

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES
SPEEDBRAKES   OPEN

DRAG CHUTE   DEPLOYED

IDLE SELECTED AND

AT REFUSAL SPEED
MAX EFFORT BRAKING
WET CONCRETE (RCR = 18)

NOTES:

COMPUTE % INCREASE/DECREASE CHANGES INDIVIDUALLY.

FOR RCR = 12 (WET) DECREASE NONAB/AB WET RUNWAY

INCREASE/DECREASE REFUSAL SPEED 2.1%/1.1% WITH

INCREASE/DECREASE REFUSAL SPEED 7/8 KIAS WITH NONAB

REFUSAL SPEED BY 6/8.5 KIAS.

NON-AB AND 2.1%/1.0% WITH AB PER 1000 LB LESS/

ADDITIONAL GW.

AND 8/9 KIAS WITH AB PER 5 KTS HEADWIND/TAILWIND.

INCREASE/DECREASE REFUSAL SPEED 0/0.5 KIAS WITH

NON-AB AND 1.5/2 KIAS WITH AB PER 1% UPSLOPE/

DOWNSLOPE.

GW = 32,000 LB

Figure P6.(Sheet 2)

T.O. GR1F16CJ1CL2

P14/PW/CFT

Refusal Speed With Drag Chute

GR1F-16CJ-1CL-1-2014X37

DRAG CHUTE DEPLOYED

DATA BASIS ESTIMATED

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES
SPEEDBRAKES   OPEN

DRAG CHUTE   DEPLOYED

IDLE SELECTED AND

AT REFUSAL SPEED
MAX EFFORT BRAKING
SNOW (RCR = 8)

NOTES:

COMPUTE % INCREASE/DECREASE CHANGES INDIVIDUALLY.

INCREASE/DECREASE REFUSAL SPEED 2.1%/1.1% WITH

INCREASE/DECREASE REFUSAL SPEED 7/8 KIAS WITH NONAB

NON-AB AND 2.0%/1.0% WITH AB PER 1000 LB LESS/

ADDITIONAL GW.

AND 9/10 KIAS WITH AB PER 5 KTS HEADWIND/TAILWIND.

INCREASE/DECREASE REFUSAL SPEED 0.5/1.5 KIAS WITH

NON-AB AND 2.0/3.5 KIAS WITH AB PER 1% UPSLOPE/

DOWNSLOPE.

GW = 32,000 LB

Figure P6.(Sheet 3)

T.O. GR1F16CJ1CL2

P15/PW/CFT

Refusal Speed With Drag Chute

GR1F-16CJ-1CL-1-2015X37

DRAG CHUTE DEPLOYED

DATA BASIS ESTIMATED

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES
SPEEDBRAKES   OPEN

DRAG CHUTE   DEPLOYED

IDLE SELECTED AND

AT REFUSAL SPEED
MAX EFFORT BRAKING
ICY (RCR = 4)

NOTES:

COMPUTE % INCREASE/DECREASE CHANGES INDIVIDUALLY.

DECREASE/INCREASE REFUSAL SPEED 2.2%/1.1% WITH

INCREASE/DECREASE REFUSAL SPEED 10/12 KIAS WITH NONAB

NON-AB AND 2.0%/1.0% WITH AB PER 1000 LB LESS/

ADDITIONAL GW.

AND 12/14 KIAS WITH AB PER 5 KTS HEADWIND/TAILWIND.

INCREASE/DECREASE REFUSAL SPEED 2.5/8.5 KIAS WITH 

NON-AB AND 5/11 KIAS WITH AB PER 1% UPSLOPE

DOWNSLOPE.

GW = 32,000 LB

Figure P6.(Sheet 4)

T.O. GR1F16CJ1CL2

P16/PW/CFT

1F-16X-1CL-1-0001X

Landing Density Factor

Figure P7.

T.O. GR1F16CJ1CL2

P17/PW/CFT

Approach Speeds

DATA BASIS ESTIMATED

ENGINE F100PW229

CONFIGURATION:

CONDITIONS

D

ALL DRAG INDEXES

D

ALL TEMPERATURES

D

ALL ALTITUDES

D

13 DEGREES AOA

(INDEXER ON SPEED)

NOTE:

ACTUAL APPROACH AIRSPEED AT 11/13 DEGREES AOA MAY DIF

FER BY +/5 KNOTS DUE TO VARIATIONS IN AIRCRAFT CG.

GROSS WEIGHT (LB)

AIRSPEED (KIAS)

19,000

132

20,000

136

21,000

139

22,000

142

23,000

146

24,000

149

25,000

152

26,000

155

27,000

158

28,000

161

29,000

164

30,000

166

31,000

169

32,000

172

33,000

174

34,000

177

35,000

180

36,000

182

37,000

185

38,000

39,000

187

190

40,000

41,000

42,000

43,000

44,000

45,000

46,000

47,000

48,000

49,000

50,000

51,000

52,000

192

195

197

199

201

204

206

208

210

213

215

217

219

NOTE: Add 8 KIAS for an

11

°

 AOA approach

Figure P8.

T.O. GR1F16CJ1CL2

P18/PW/CFT

GR1F-16CJ-1CL-1-2017X37

Short Field Landing Distance

DATA BASIS ESTIMATED

ENGINE F100-PW-229

NOTES:

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES

TOUCHDOWN AT 13

DEGREES AOA

ZERO WIND AND SLOPE

IDLE

SPEEDBRAKES   OPEN

MAX EFFORT BRAKING

COMPUTE % INCREASE/DECREASE CHANGES

INDIVIDUALLY.

DECREASE DISTANCE 1.5% PER 1 KT HEADWIND.

INCREASE DISTANCE 2.2% PER 1 KT TAILWIND.

DECREASE DISTANCE 5.0% PER 1% UPSLOPE.

INCREASE DISTANCE 7.0% PER 1% DOWNSLOPE.

Figure P9.(Sheet 1)

T.O. GR1F16CJ1CL2

P19/PW/CFT

GR1F-16CJ-1CL-1-2018X37

Short Field Landing Distance

DATA BASIS ESTIMATED

ENGINE F100-PW-229

NOTES:

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES

TOUCHDOWN AT 13

DEGREES AOA

ZERO WIND AND SLOPE

IDLE

SPEEDBRAKES   OPEN

MAX EFFORT BRAKING

COMPUTE % INCREASE/DECREASE CHANGES

INDIVIDUALLY.

DECREASE DISTANCE 1.5% PER 1 KT HEADWIND.

INCREASE DISTANCE 2.2% PER 1 KT TAILWIND.

DECREASE DISTANCE 5.0% PER 1% UPSLOPE.

INCREASE DISTANCE 7.0% PER 1% DOWNSLOPE.

Figure P9.(Sheet 2)

T.O. GR1F16CJ1CL2

P20/PW/CFT

GR1F-16CJ-1CL-1-2019X37

DATA BASIS ESTIMATED

ENGINE F100-PW-229

NOTES:

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES

TOUCHDOWN AT 13

DEGREES AOA

ZERO WIND AND SLOPE

IDLE

SPEEDBRAKES   OPEN

MAX EFFORT BRAKING

COMPUTE % INCREASE/DECREASE CHANGES

INDIVIDUALLY.

DECREASE DISTANCE 1.5% PER 1 KT HEADWIND.

INCREASE DISTANCE 2.2% PER 1 KT TAILWIND.

DECREASE DISTANCE 5.0% PER 1% UPSLOPE.

INCREASE DISTANCE 7.0% PER 1% DOWNSLOPE.

Short Field Landing Distance    SEC

Figure P9.(Sheet 3)

T.O. GR1F16CJ1CL2

P21/PW/CFT

GR1F-16CJ-1CL-1-2021X37

COMPUTE % INCREASE/DECREASE CHANGES

INDIVIDUALLY.
DECREASE DISTANCE 1.5% PER 1 KT HEADWIND.
INCREASE DISTANCE 2.2% PER 1 KT TAILWIND.
DECREASE DISTANCE 5.0% PER 1% UPSLOPE.
INCREASE DISTANCE 7.0% PER 1% DOWNSLOPE.

Short Field Landing Distance With Drag

Chute

DATA BASIS ESTIMATED

NOTES:

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES

SPEEDBRAKES   OPEN

DRAG CHUTE   DEPLOYED

TOUCHDOWN AT 13

DEGREES AOA

ZERO WIND AND

SLOPE

IDLE
MAX EFFORT BRAKING

BELOW 170 KNOTS

Figure P9.(Sheet 4)

T.O. GR1F16CJ1CL2

P22/PW/CFT

GR1F-16CJ-1CL-1-2022X37

Short Field Landing Distance With Drag

Chute

DATA BASIS ESTIMATED

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

COMPUTE % INCREASE/DECREASE CHANGES

INDIVIDUALLY.
DECREASE DISTANCE 1.5% PER 1 KT HEADWIND.
INCREASE DISTANCE 2.2% PER 1 KT TAILWIND.
DECREASE DISTANCE 5.0% PER 1% UPSLOPE.
INCREASE DISTANCE 7.0% PER 1% DOWNSLOPE.

NOTES:

ALL DRAG INDEXES

SPEEDBRAKES   OPEN

DRAG CHUTE   DEPLOYED

TOUCHDOWN AT 13

DEGREES AOA

ZERO WIND AND

SLOPE

IDLE
MAX EFFORT BRAKING

BELOW 170 KNOTS

Figure P9.(Sheet 5)

T.O. GR1F16CJ1CL2

P23/PW/CFT

GR1F-16CJ-1CL-1-2023X37

COMPUTE % INCREASE/DECREASE CHANGES

INDIVIDUALLY.
DECREASE DISTANCE 1.5% PER 1 KT HEADWIND.
INCREASE DISTANCE 2.2% PER 1 KT TAILWIND.
DECREASE DISTANCE 5.0% PER 1% UPSLOPE.
INCREASE DISTANCE 7.0% PER 1% DOWNSLOPE.

Short Field Landing Distance    SEC With

Drag Chute

DATA BASIS ESTIMATED

NOTES:

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES

SPEEDBRAKES   OPEN

DRAG CHUTE   DEPLOYED

TOUCHDOWN AT 13

DEGREES AOA

ZERO WIND AND

SLOPE

IDLE
MAX EFFORT BRAKING

BELOW 170 KNOTS

Figure P9.(Sheet 6)

T.O. GR1F16CJ1CL2

P24/PW/CFT

GR1F-16CJ-1CL-1-2024X37

COMPUTE % INCREASE/DECREASE CHANGES

INDIVIDUALLY.
DECREASE DISTANCE 1.5% PER 1 KT HEADWIND.
INCREASE DISTANCE 2.2% PER 1 KT TAILWIND.
DECREASE DISTANCE 5.0% PER 1% UPSLOPE.
INCREASE DISTANCE 7.0% PER 1% DOWNSLOPE.

Short Field Landing Distance    SEC With

Drag Chute

DATA BASIS ESTIMATED

NOTES:

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES

SPEEDBRAKES   OPEN

DRAG CHUTE   DEPLOYED

TOUCHDOWN AT 13

DEGREES AOA

ZERO WIND AND

SLOPE

IDLE
MAX EFFORT BRAKING

BELOW 170 KNOTS

Figure P9.(Sheet 7)

T.O. GR1F16CJ1CL2

P25/PW/CFT

Climb/Optimum Cruise Drag Index = 0

DATA BASIS ESTIMATED

ENGINE F100PW229

FUEL

JP8

NOTES:

D

STD DAY/FULLY SERVICED FUEL = 10,172 LB.

D

800LB FUEL ALLOWANCE FOR GROUND OPERATION AND

TAKEOFF/ACCELERATION TO MIL CLIMB AIRSPEED

(ASSUME 30MIN GROUND TIME).

D

CLIMB AT KIAS/MACH NO., WHICHEVER IS SLOWER.

MIL CLIMB

OPTIMUM CRUISE

AT LEVEL OFF

ALT

1000

FEET

CLIMB

@

KIAS

MACH

TIME

(MIN)

DIST

(NM)

FUEL REMAINING

AT

LEVEL OFF

(LB)

MACH/KIAS/KTAS

TOTAL

FUEL FLOW

(LB/HR)

45

--- --- ---

---

---

---

40

445

0.83

7.1

52.7

8613

0.83/252/474

2479

35

445

0.84

3.8

31.4

8785

0.84/288/485

2697

30

445

0.80

2.8

22.3

8891

0.80/304/471

2776

25

445

0.76

2.1

16.0

8981

0.76/321/460

2967

20

445

0.70

1.5

10.7

9077

0.70/324/430

3068

10

0.60

0.7

4.1

9221

0.60/333/383

3417

 0

0.51

0.0

0.0

9372

0.51/335/335

3756

OPTIMUM CRUISE

7000 LB REMAINING

5000 LB REMAINING

2000 LB REMAINING

ALT

1000

FEET

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

45

---

---

---

---

---

---

40 0.87/268/501 2691 0.87/268/502 2488 0.84/256/482 2148
35 0.84/286/483 2561 0.81/276/468 2352 0.80/272/461 2136
30 0.80/304/471 2665 0.80/304/471 2555 0.76/289/450 2309
25 0.75/315/452 2811 0.73/307/440 2655 0.70/293/421 2418
20 0.70/324/430 2980 0.70/323/429 2897 0.66/302/403 2609
10 0.60/333/383 3330 0.58/322/370 3143 0.54/299/345 2821

 0

0.50/330/330 3616 0.48/321/321 3439 0.45/300/300 3115

Figure P10.(Sheet 1)

T.O. GR1F16CJ1CL2

P26/PW/CFT

Climb/Optimum Cruise   Drag Index = 22

DATA BASIS FLIGHT ESTIMATED

ENGINE

F100PW229

FUEL

JP8

NOTES:

D

STD DAY/FULLY SERVICED FUEL = 10,172 LB + 2040 LB=

12,212 LB.

D

800LB FUEL ALLOWANCE FOR GROUND OPERATION AND

TAKEOFF/ACCELERATION TO MIL CLIMB AIRSPEED (AS

SUME 30MIN GROUND TIME).

D

CLIMB AT KIAS/MACH NO., WHICHEVER IS SLOWER.

MIL CLIMB

OPTIMUM CRUISE

AT LEVEL OFF

ALT

1000

FEET

CLIMB

@

KIAS

MACH

TIME

(MIN)

DIST

(NM)

FUEL REMAINING

AT

LEVEL OFF

(LB)

MACH/KIAS/KTAS

TOTAL

FUEL FLOW

(LB/HR)

45

--- --- ---

---

---

---

40

441

0.87

8.0

67.5

10,454

0.87/268/501

3331

35

441

0.85

4.6

38.2

10,712

0.85/291/490

3078

30

441

0.80

3.3

26.4

10,850

0.80/304/472

3082

25

441

0.77

2.4

18.9

10,956

0.77/325/465

3295

20

441

0.70

1.7

12.4

11,072

0.70/324/430

3319

10

0.60

0.8

4.7

11,242

0.60/333/383

3667

 0

0.52

0.0

0.0

11,412

0.52/343/343

4099

OPTIMUM CRUISE

7000 LB REMAINING

5000 LB REMAINING

2000 LB REMAINING

ALT

1000

FEET

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

45

---

---

---

---

---

---

40 0.85/259/488 2797 0.85/259/487 2597 0.84/256/482 2298
35 0.83/283/479 2704 0.80/272/461 2468 0.80/272/461 2277
30 0.80/304/471 2838 0.79/301/467 2704 0.75/283/442 2399
25 0.74/311/446 2951 0.72/300/432 2754 0.70/293/421 2545
20 0.70/323/430 3133 0.69/317/421 2991 0.64/297/396 2694
10 0.59/329/378 3446 0.57/315/362 3227 0.53/294/338 2899

 0

0.49/326/326 3731 0.48/314/314 3517 0.45/295/295 3192

Figure P10.(Sheet 2)

T.O. GR1F16CJ1CL2

P27/PW/CFT

Climb/Optimum Cruise   Drag Index = 53

DATA BASIS ESTIMATED

ENGINE F100PW229

FUEL

JP8

NOTES:

D

STD DAY/FULLY SERVICED FUEL = 10,172 LB + 5032 LB=

15,204 LB.

D

800LB FUEL ALLOWANCE FOR GROUND OPERATION AND

TAKEOFF/ACCELERATION TO MIL CLIMB AIRSPEED (AS

SUME 30MIN GROUND TIME).

D

CLIMB AT KIAS/MACH NO., WHICHEVER IS SLOWER.

MIL CLIMB

OPTIMUM CRUISE

AT LEVEL OFF

ALT

1000

FEET

CLIMB

@

KIAS

MACH

TIME

(MIN)

DIST

(NM)

FUEL REMAINING

AT

LEVEL OFF

(LB)

MACH/KIAS/KTAS

TOTAL

FUEL FLOW

(LB/HR)

40

--- --- ---

---

---

---

35

434

0.85

6.2

51.4

13,500

0.85/291/490

3606

30

434

0.82

4.2

33.6

13,700

0.82/311/481

3621

25

434

0.78

3.0

23.4

13,845

0.78/329/471

3777

20

434

0.71

2.1

15.2

13,991

0.71/327/434

3754

10

0.60

0.9

5.5

14,206

0.60/335/384

4034

 0

0.53

0.0

0.0

14,404

0.53/350/350

4552

OPTIMUM CRUISE

10,000 LB REMAINING 7000 LB REMAINING

2000 LB REMAINING

ALT

1000

FEET

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

40

---

---

---

---

---

---

35 0.84/287/484 3215 0.83/282/476 2904 0.80/272/461 2453
30 0.80/304/471 3256 0.80/303/471 3059 0.74/281/439 2568
25 0.75/315/452 3378 0.72/302/434 3079 0.70/292/421 2720
20 0.70/324/430 3494 0.70/323/429 3335 0.63/288/384 2777
10 0.60/333/383 3826 0.57/318/365 3529 0.51/285/328 2970

 0

0.50/330/330 4109 0.48/316/316 3809 0.43/287/287 3272

Figure P10.(Sheet 3)

T.O. GR1F16CJ1CL2

P28/PW/CFT

Climb/Optimum Cruise   Drag Index = 79

DATA BASIS ESTIMATED

ENGINE F100PW229

FUEL

JP8

NOTES:

D

STD DAY/FULLY SERVICED FUEL = 10,172 LB + 5032 LB

+ 2040 LB = 17,244 LB.

D

1400LB FUEL ALLOWANCE FOR GROUND OPERATION

AND MAX AB TAKEOFF/ACCELERATION TO MIL CLIMB AIR

SPEED (ASSUME 30MIN GROUND TIME).

D

TAKEOFF AND CLIMB TO MIL CLIMB AIRSPEED WITH MAX

AB.

D

CLIMB AT KIAS/MACH NO., WHICHEVER IS SLOWER.

MIL CLIMB

OPTIMUM CRUISE

AT LEVEL OFF

ALT

1000

FEET

CLIMB

@

KIAS

MACH

TIME

(MIN)

DIST

(NM)

FUEL REMAINING

AT

LEVEL OFF

(LB)

MACH/KIAS/KTAS

TOTAL

FUEL FLOW

(LB/HR)

40

--- --- ---

---

---

---

35

421

0.85

8.2

67.0

14,718

0.85/291/490

4026

30

421

0.82

5.0

40.0

15,014

0.82/313/484

3996

25

421

0.78

3.5

27.2

15,198

0.78/329/470

4112

20

421

0.70

2.4

17.4

15,371

0.70/326/433

4050

10

0.60

1.0

6.1

15,626

0.60/334/383

4297

 0

0.53

0.0

0.0

15,844

0.53/354/354

4868

OPTIMUM CRUISE

12,000 LB REMAINING 7000 LB REMAINING

2000 LB REMAINING

ALT

1000

FEET

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

MACH/KIAS/

KTAS

TOTAL

FUEL

FLOW

(LB/HR)

40

---

---

---

---

---

---

35 0.85/291/490 3695 0.83/282/476 3105 0.79/268/455 2591
30 0.80/304/472 3636 0.78/297/462 3203 0.73/276/432 2694
25 0.75/315/452 3735 0.71/296/427 3208 0.69/288/416 2856
20 0.70/324/430 3818 0.67/309/411 3383 0.62/285/381 2893
10 0.60/333/383 4105 0.57/314/361 3653 0.52/285/329 3118

 0

0.51/336/336 4453 0.47/313/313 3939 0.43/284/284 3371

Figure P10.(Sheet 4)

 

 

 

 

 

 

 

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