F16C/D. FLIGHT MANUAL (2002) - page 36

T.O. GR1F16CJ1CL2

P17/PW

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

192

195

197

199

201

204

206

208

210

NOTE: Add 8 KIAS for an

11

°

 AOA approach

Figure P8.

T.O. GR1F16CJ1CL2

P18/PW

1F-16CJ-1CL-1-0011A

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

1F-16CJ-1CL-1-0012A

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

1F-16CJ-1CL-1-0013B

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

GR1F-16CJ-1CL-1-1021X37

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

GR1F-16CJ-1CL-1-1022X37

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 5)

T.O. GR1F16CJ1CL2

P23/PW

GR1F-16CJ-1CL-1-1023X37

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

GR1F-16CJ-1CL-1-1024X37

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

Climb/Optimum Cruise Drag Index = 0

DATA BASIS FLIGHT TEST

ENGINE F100PW229

FUEL

JP8

NOTES:

D

STD DAY/FULLY SERVICED FUEL = 7162 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)

50

--- --- ---

---

---

---

45

445

0.87

7.6

63.4

5584

0.87/238/502

2622

40

445

0.87

4.5

37.4

5764

0.87/268/502

2454

35

445

0.81

3.2

25.3

5880

0.81/275/466

2327

30

445

0.80

2.4

18.4

5957

0.80/304/471

2541

25

445

0.73

1.8

13.0

6038

0.73/308/442

2655

20

445

0.70

1.3

8.8

6112

0.70/323/430

2889

10

0.59

0.6

3.4

6231

0.59/325/374

3171

 0

0.49

0.0

0.0

6362

0.49/326/326

3488

OPTIMUM CRUISE

5000 LB REMAINING

3000 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)

50

---

---

---

---

---

---

45 0.87/238/502 2540 0.85/231/488 2232 0.85/231/488 2128
40 0.87/268/501 2384 0.84/256/482 2139 0.84/256/482 2069
35 0.80/272/461 2249 0.80/272/461 2127 0.80/272/461 2070
30 0.80/304/471 2496 0.76/289/450 2303 0.75/283/442 2220
25 0.72/301/433 2560 0.70/293/421 2408 0.70/293/421 2369
20 0.69/318/423 2804 0.66/304/405 2609 0.64/297/396 2514
10 0.57/316/363 3040 0.54/301/346 2824 0.53/293/338 2715

 0

0.48/316/316 3338 0.46/302/302 3118 0.45/295/295 3008

Figure P10.(Sheet 1)

T.O. GR1F16CJ1CL2

P26/PW

Climb/Optimum Cruise   Drag Index = 22

DATA BASIS FLIGHT TEST

ENGINE F100PW229

FUEL

JP8

NOTES:

D

STD DAY/FULLY SERVICED FUEL = 7162 LB + 2040 LB=

9202 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

436

0.85

5.8

47.2

7677

0.85/259/488

2750

35

436

0.83

3.8

30.9

7821

0.83/282/476

2668

30

436

0.80

2.8

22.1

7924

0.80/304/471

2823

25

436

0.74

2.1

15.6

8019

0.74/312/447

2947

20

436

0.70

1.5

10.5

8108

0.70/324/430

3126

10

0.60

0.7

3.9

8255

0.60/332/382

3477

 0

0.50

0.0

0.0

8402

0.50/330/330

3776

OPTIMUM CRUISE

5000 LB REMAINING

3000 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 0.85/259/486 2488 0.84/256/482 2291 0.84/256/482 2214
35 0.80/272/461 2393 0.80/272/461 2269 0.80/272/461 2210
30 0.78/295/459 2591 0.75/283/442 2389 0.75/283/442 2343
25 0.70/293/421 2625 0.70/293/421 2536 0.70/293/421 2495
20 0.67/311/414 2892 0.65/297/397 2691 0.63/291/388 2594
10 0.56/309/356 3120 0.53/295/340 2904 0.52/288/331 2789

 0

0.47/310/310 3421 0.45/297/297 3197 0.44/289/289 3081

Figure P10.(Sheet 2)

T.O. GR1F16CJ1CL2

P27/PW

Climb/Optimum Cruise   Drag Index = 53

DATA BASIS FLIGHT TEST

ENGINE F100PW229

FUEL

JP8

NOTES:

D

STD DAY/FULLY SERVICED FUEL = 7162 LB + 5032 LB=

12,194 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

424

0.85

9.1

74.1

10,363

0.85/259/488

3322

35

424

0.84

5.0

40.7

10,650

0.84/287/484

3170

30

424

0.80

3.6

27.9

10,798

0.80/304/471

3229

25

424

0.75

2.6

19.4

10,921

0.75/315/451

3361

20

424

0.70

1.8

13.0

11,034

0.70/324/430

3482

10

0.60

0.8

4.7

11,222

0.60/333/383

3822

 0

0.50

0.0

0.0

11,394

0.50/331/331

4116

OPTIMUM CRUISE

8000 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 3012 0.84/256/482 2655 0.84/256/482 2395
35 0.82/281/475 2891 0.80/272/461 2577 0.78/265/451 2335
30 0.80/304/471 3051 0.76/286/446 2718 0.73/276/431 2460
25 0.72/302/434 3070 0.70/293/421 2815 0.69/288/415 2624
20 0.70/323/429 3322 0.65/301/402 2982 0.61/282/377 2677
10 0.57/319/367 3532 0.54/299/345 3193 0.50/279/322 2858

 0

0.48/318/318 3814 0.45/301/301 3493 0.43/282/282 3161

Figure P10.(Sheet 3)

T.O. GR1F16CJ1CL2

P28/PW

Climb/Optimum Cruise   Drag Index = 79

DATA BASIS FLIGHT TEST

ENGINE F100PW229

FUEL

JP8

NOTES:

D

STD DAY/FULLY SERVICED FUEL = 7162 LB + 5032 LB

+ 2040 LB = 14,234 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

411

0.84

6.2

50.3

11,938

0.84/287/484

3518

30

411

0.80

4.2

32.9

12,138

0.80/304/471

3550

25

411

0.75

3.0

22.5

12,287

0.75/315/451

3670

20

411

0.70

2.1

15.0

12,420

0.70/324/430

3771

10

0.60

0.9

5.3

12,644

0.60/333/383

4075

 0

0.51

0.0

0.0

12,834

0.51/334/334

4412

OPTIMUM CRUISE

9000 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)

40

---

---

---

---

---

---

35 0.84/285/482 3221 0.80/272/461 2757 0.77/262/446 2464
30 0.80/303/471 3321 0.75/283/442 2867 0.72/271/425 2582
25 0.71/299/430 3287 0.70/293/421 2987 0.68/283/409 2747
20 0.68/315/419 3484 0.64/293/391 3057 0.61/279/374 2787
10 0.58/319/367 3751 0.54/297/342 3323 0.50/279/322 2998

 0

0.48/318/318 4035 0.45/296/296 3590 0.42/278/278 3253

Figure P10.(Sheet 4)

T.O. GR1F16CJ1CL2

P29/PW

Diversion Decision   Divert

DATA BASIS FLIGHT TEST

ENGINE F100PW229

CONDITIONS:

D

MIL CLIMB AT 423 KIAS OR

OPTIMUM ALTITUDE MACH

NO., WHICHEVER IS LESS

D

DESCEND AT IDLE,

221 KIAS

D

STANDARD DAY

D

NO FUEL RESERVE

D

ZERO WIND

D

ALL DESCENTS ARE

TO SEA LEVEL

D

DRAG INDEX = 55

NOTES:

D

4.0% RANGE GAIN FOR 10 KTS TAILWIND.

D

2.5% RANGE LOSS FOR 10 KTS HEADWIND.

D

SUBTRACT 2.5 NM FROM DESCENT DISTANCE FOR EACH

1000 FT OF DESTINATION ELEVATION.

D

TOTAL DIVERT RANGE AT CURRENT ALTITUDE INCLUDES

CRUISE AND DESCENT, AND TOTAL DIVERT RANGE AT OPTI

MUM ALTITUDE INCLUDES CLIMB, CRUISE, AND DESCENT.

IF YOU ARE AT SEA LEVEL

FUEL

ON

REMAIN

AT SEA LEVEL

CLIMB TO OPT ALTITUDE

DESCEND

ON

BOARD

AT SEA LEVEL

TOTAL

FROM

FUEL USED

BOARD

-LB

TOTAL DIVERT

RANGE-NM

ALT/MACH

TOTAL

DIVERT

RANGE-NM

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

19

5.0K/0.45

20

16

104

400

37

15.0K/0.54

46

39

204

600

55

25.0K/0.69

78

62

275

800

73 0.42M

30.0K/0.71

113

72

306

1000

91

35.0K/0.76

151

85

338

1500

136

40.0K/0.82

250

99

376

2000

180

40.0K/0.83

349

99

376

IF YOU ARE AT 5000 FEET

FUEL

ON

REMAIN

AT 5000 FT

CLIMB TO OPT ALTITUDE

DESCEND

ON

BOARD

AT 5000 FT

TOTAL

FROM

FUEL USED

BOARD

-LB

TOTAL DIVERT

RANGE-NM*

ALT/MACH

TOTAL

DIVERT

RANGE-NM

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

26

5.0K/0.45

26

16

104

400

46

15.0K/0.54

52

39

204

600

66

30.0K/0.72

88

72

306

800

87 0.46M

35.0K/0.76

124

85

338

1000

107

35.0K/0.77

163

85

338

1500

157

40.0K/0.83

263

99

376

2000

207

40.0K/0.84

362

99

376

*START DESCENT AT 16 NM. 104 LB FUEL USED IN DESCENT.

Figure P11.(Sheet 1)

T.O. GR1F16CJ1CL2

P30/PW

Diversion Decision   Divert

DATA BASIS FLIGHT TEST

ENGINE F100PW229

CONDITIONS:

D

MIL CLIMB AT 423 KIAS OR

OPTIMUM ALTITUDE MACH

NO., WHICHEVER IS LESS

D

DESCEND AT IDLE,

221 KIAS

D

STANDARD DAY

D

NO FUEL RESERVE

D

ZERO WIND

D

ALL DESCENTS ARE

TO SEA LEVEL

D

DRAG INDEX = 55

NOTES:

D

4.0% RANGE GAIN FOR 10 KTS TAILWIND.

D

2.5% RANGE LOSS FOR 10 KTS HEADWIND.

D

SUBTRACT 2.5 NM FROM DESCENT DISTANCE FOR EACH

1000 FT OF DESTINATION ELEVATION.

D

TOTAL DIVERT RANGE AT CURRENT ALTITUDE INCLUDES

CRUISE AND DESCENT, AND TOTAL DIVERT RANGE AT OPTI

MUM ALTITUDE INCLUDES CLIMB, CRUISE, AND DESCENT.

IF YOU ARE AT 10,000 FEET

FUEL

ON

REMAIN

AT 10 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

ON

BOARD

AT 10,000 FT

TOTAL

FROM

FUEL USED

BOARD

-LB

TOTAL DIVERT

RANGE-NM*

ALT/MACH

TOTAL

DIVERT

RANGE-NM

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

32

10.0K/0.50

32

28

164

400

55

20.0K/0.60

60

49

239

600

78

30.0K/0.71

97

72

306

800

101 0.50M

35.0K/0.76

136

85

338

1000

123

35.0K/0.77

175

85

338

1500

180

40.0K/0.83

275

99

376

2000

236

40.0K/0.84

374

99

376

*START DESCENT AT 28 NM. 164 LB FUEL USED IN DESCENT.

IF YOU ARE AT 20,000 FEET

FUEL

ON

REMAIN

AT 20 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

ON

BOARD

AT 20,000 FT

TOTAL

FROM

FUEL USED

BOARD

-LB

TOTAL DIVERT

RANGE-NM*

ALT/MACH

TOTAL

DIVERT

RANGE-NM

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

 

 

 

 

 

400

72

25.0K/0.70

76

62

275

600

101

35.0K/0.76

114

85

338

800

130 0.61M

40.0K/0.82

155

99

376

1000

158

40.0K/0.82

196

99

376

1500

229

40.0K/0.83

298

99

376

2000

299

40.0K/0.84

397

99

376

*START DESCENT AT 49 NM. 239 LB FUEL USED IN DESCENT.

Figure P11.(Sheet 2)

T.O. GR1F16CJ1CL2

P31/PW

Diversion Decision   Divert

DATA BASIS FLIGHT TEST

ENGINE F100PW229

CONDITIONS:

D

MIL CLIMB AT 423 KIAS OR

OPTIMUM ALTITUDE MACH

NO., WHICHEVER IS LESS

D

DESCEND AT IDLE,

221 KIAS

D

STANDARD DAY

D

NO FUEL RESERVE

D

ZERO WIND

D

ALL DESCENTS ARE

TO SEA LEVEL

D

DRAG INDEX = 55

NOTES:

D

4.0% RANGE GAIN FOR 10 KTS TAILWIND.

D

2.5% RANGE LOSS FOR 10 KTS HEADWIND.

D

SUBTRACT 2.5 NM FROM DESCENT DISTANCE FOR EACH

1000 FT OF DESTINATION ELEVATION.

D

TOTAL DIVERT RANGE AT CURRENT ALTITUDE INCLUDES

CRUISE AND DESCENT, AND TOTAL DIVERT RANGE AT OPTI

MUM ALTITUDE INCLUDES CLIMB, CRUISE, AND DESCENT.

IF YOU ARE AT 30,000 FEET

FUEL

ON

REMAIN

AT 30 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

ON

BOARD

AT 30,000 FT

TOTAL

FROM

FUEL USED

BOARD

-LB

TOTAL DIVERT

RANGE-NM*

ALT/MACH

TOTAL

DIVERT

RANGE-NM

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

 

 

 

 

 

400

89

30.0K/0.71

89

72

306

600

125

40.0K/0.82

131

99

376

800

161 0.72M

40.0K/0.82

172

99

376

1000

196

40.0K/0.82

213

99

376

1500

284

40.0K/0.83

314

99

376

2000

371

40.0K/0.84

414

99

376

*START DESCENT AT 72 NM. 306 LB FUEL USED IN DESCENT.

IF YOU ARE AT 40,000 FEET

FUEL

ON

REMAIN

AT 40 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

ON

BOARD

AT 40,000 FT

TOTAL

FROM

FUEL USED

BOARD

-LB

TOTAL DIVERT

RANGE-NM*

ALT/MACH

TOTAL

DIVERT

RANGE-NM

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

 

 

 

 

 

400

104

40.0K/0.82

104

99

376

600

146

40.0K/0.82

146

99

376

800

187 0.83M

40.0K/0.82

187

99

376

1000

228

40.0K/0.83

228

99

376

1500

330

40.0K/0.84

330

99

376

2000

429

40.0K/0.84

429

99

376

*START DESCENT AT 99 NM. 376 LB FUEL USED IN DESCENT.

Figure P11.(Sheet 3)

T.O. GR1F16CJ1CL2

P32/PW

Diversion Decision   Loiter

DATA BASIS FLIGHT TEST

ENGINE F100PW229

CONDITIONS:

D

MIL CLIMB AT 423 KIAS OR

OPTIMUM ALTITUDE MACH

NO., WHICHEVER IS LESS

D

DESCEND AT IDLE,

221 KIAS

D

STANDARD DAY

D

NO FUEL RESERVE

D

ZERO WIND

D

ALL DESCENTS ARE

TO SEA LEVEL

D

DRAG INDEX = 55

NOTES:

D

LOITER TIME AT CONSTANT ALTITUDE BASED ON 10 NM

HOLDING PATTERN WITH 30DEGREE BANK TURNS.

D

ADD 0.5 MIN TO LOITER TIME FOR EACH 1000 FT OF DES

TINATION ELEVATION.

D

SUBTRACT 2.3 NM FROM DESCENT DISTANCE FOR EACH

1000 FT OF DESTINATION ELEVATION.

D

TOTAL LOITER TIME AT CURRENT ALTITUDE INCLUDES LOI

TER AND DESCENT, AND TOTAL TIME AT OPTIMUM ALTI

TUDE INCLUDES CLIMB, LOITER, AND DESCENT.

IF YOU ARE AT SEA LEVEL

FUEL

ON

REMAIN

AT SEA LEVEL

CLIMB TO OPT ALTITUDE

DESCEND

ON

BOARD

AT SEA LEVEL

TOTAL

FROM

FUEL USED

BOARD

-LB

TOTAL LOITER

TIME-MIN

ALT/MACH

TOTAL

TIME-MIN

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

 

 

 

 

 

400

9

0.0K/0.31

9

0

0

600

13

5.0K/0.34

14

13

87

800

18 0.32M

20.0K/0.46

20

45

228

1000

22

30.0K/0.56

26

67

292

1500

32

35.0K/0.66

40

80

327

2000

42

35.0K/0.66

52

80

327

IF YOU ARE 5000 FEET

FUEL

ON

REMAIN

AT 5000 FT

CLIMB TO OPT ALTITUDE

DESCEND

ON

BOARD

AT 5000 FT

TOTAL

FROM

FUEL USED

BOARD

-LB

TOTAL LOITER

TIME-MIN*

ALT/MACH

TOTAL

TIME-MIN

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

 

 

 

 

 

400

 

 

 

 

 

600

15

10.0K/0.38

16

24

149

800

20 0.35M

25.0K/0.50

22

56

260

1000

24

35.0K/0.66

28

80

327

1500

35

35.0K/0.66

41

80

327

2000

45

35.0K/0.66

53

80

327

* START DESCENT AT 13 NM. 87 LB FUEL USED IN DESCENT.

Figure P12.(Sheet 1)