F16C/D. FLIGHT MANUAL (2002) - page 37

T.O. GR1F16CJ1CL2

P33/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 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 LOITER

TIME-MIN*

ALT/MACH

TOTAL

TIME-MIN

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

 

 

 

 

 

400

 

 

 

 

 

600

17

15.0K/0.42

17

35

193

800

22 0.38M

25.0K/0.50

23

56

260

1000

26

35.0K/0.66

29

80

327

1500

38

35.0K/0.66

42

80

327

2000

48

35.0K/0.66

54

80

327

* START DESCENT AT 25 NM. 150 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 LOITER

TIME-MIN*

ALT/MACH

TOTAL

TIME-MIN

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

 

 

 

 

 

400

 

 

 

 

 

600

20

25.0K/0.50

21

56

260

800

25 0.47M

35.0K/0.66

26

80

327

1000

30

35.0K/0.66

32

80

327

1500

42

35.0K/0.66

44

80

327

2000

53

35.0K/0.66

56

80

327

* START DESCENT AT 46 NM. 229 LB FUEL USED IN DESCENT.

Figure P12.(Sheet 2)

T.O. GR1F16CJ1CL2

P34/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 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 LOITER

TIME-MIN*

ALT/MACH

TOTAL

TIME-MIN

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

 

 

 

 

 

400

 

 

 

 

 

600

23

30.0K/0.56

23

67

292

800

28 0.57M

35.0K/0.66

29

80

327

1000

34

35.0K/0.66

34

80

327

1500

46

35.0K/0.66

46

80

327

2000

58

35.0K/0.66

58

80

327

* START DESCENT AT 67 NM. 292 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 LOITER

TIME-MIN*

ALT/MACH

TOTAL

TIME-MIN

FROM

OPT ALT

-NM

FUEL USED

IN DESCENT

-LB

200

 

 

 

 

 

400

 

 

 

 

 

600

 

 

 

 

 

800

30 0.73M

40.0K/0.73

30

95

365

1000

35

40.0K/0.73

35

95

365

1500

47

40.0K/0.73

47

95

365

2000

58

40.0K/0.73

58

95

365

* START DESCENT AT 95 NM. 365 LB FUEL USED IN DESCENT.

Figure P12.(Sheet 3)

T.O. GR1F16CJ1CL2

P35/PW

Best Cruise Altitude for Short Range 

Mission   Maximum Range Descent

DATA BASIS FLIGHT TEST

ENGINE F100PW229

CONDITIONS:

D

STANDARD DAY

D

NO WIND

D

MIL CLIMB AT SCHEDULED

KIAS OR CONSTANT

ALTITUDE OPTIMUM

CRUISE MACH NO.,

WHICHEVER IS LOWER

D

CRUISE AT CONSTANT ALTI

TUDE AT OPTIMUM MACH

D

DESCEND AT IDLE WITH

SPEEDBRAKES CLOSED

D

DRAG INDEX/DESCENT

SPEED KIAS = 0/215,

50/220, AND 

 100/230

ST CL

GW*

TOT

MSN

RG**

BEST

CR

ALT

TOTAL FUEL CONSUMED (LB)/DESCENT

RANGE (NM)

LB-

1000

NM

FT-

1000

DI

0

DI

100

DI

200

20.0

20.0

20.0

20.0

20.0

50

100

150

200

250

14.4

30.1

40.1

41.8

41.9

400/46

669/88

899/125

1099/134

1292/136

448/32

733/62

993/86

1236/91

1471/91

503/25

831/49

1140/68

1166/70

1321/71

24.0

24.0

24.0

24.0

24.0

50

100

150

200

250

15.6

29.5

34.4

36.5

37.8

414/45

717/79

966/93

1195/99

1423/105

463/35

803/62

1098/73

1378/77

1652/81

528/28

918/51

1276/60

1591/64

1895/66

28.0

28.0

28.0

28.0

28.0

50

100

150

200

250

16.8

27.2

32.5

35.0

35.7

431/43

775/66

1054/77

1317/84

1566/86

488/36

880/56

1220/67

1533/72

1842/74

561/30

1012/47

1416/57

1793/62

2159/63

32.0

32.0

32.0

32.0

32.0

50

100

150

200

250

15.4

24.9

30.1

32.9

34.0

462/36

839/54

1151/64

1447/70

1733/73

530/32

961/49

1346/60

1694/65

2042/67

609/28

1112/43

1564/52

1996/57

2402/59

*CLIMB BEGINS AT SL.

**CLIMB/CRUISE/DESCENT.

Figure P13.(Sheet 1)

T.O. GR1F16CJ1CL2

P36/PW

Best Cruise Altitude for Short Range

Mission   Maximum Range Descent

DATA BASIS FLIGHT TEST

ENGINE F100PW229

CONDITIONS:

D

STANDARD DAY

D

NO WIND

D

MIL CLIMB AT SCHEDULED

KIAS OR CONSTANT

ALTITUDE OPTIMUM

CRUISE MACH NO.,

WHICHEVER IS LOWER

D

CRUISE AT CONSTANT ALTI

TUDE AT OPTIMUM MACH

D

DESCEND AT IDLE WITH

SPEEDBRAKES CLOSED

D

DRAG INDEX/DESCENT

SPEED KIAS = 0/215,

50/220, AND 

 100/230

ST CL

GW*

TOT

MSN

RG**

BEST

CR

ALT

TOTAL FUEL CONSUMED (LB)/DESCENT

RANGE (NM)

LB-

1000

NM

FT-

1000

DI

0

DI

100

DI

200

36.0

36.0

36.0

36.0

36.0

50

100

150

200

250

13.2

22.2

28.2

30.6

31.6

493/30

906/44

1258/54

1584/59

1905/61

573/26

1049/41

1475/52

1866/57

2257/59

662/23

1218/37

1725/47

2203/51

2656/53

40.0

40.0

40.0

40.0

40.0

50

100

150

200

250

10.8

20.2

26.1

28.5

29.3

523/25

975/38

1362/46

1731/50

2082/52

617/21

1139/35

1610/46

2050/49

2477/51

714/19

1325/32

1884/41

2413/45

2916/47

44.0

44.0

44.0

44.0

44.0

50

100

150

200

250

7.6

18.6

24.2

26.1

27.1

548/20

1045/33

1470/40

1866/43

2257/44

655/16

1232/31

1748/40

2231/43

2702/44

765/14

1435/28

2047/36

2625/39

3186/41

48.0

48.0

48.0

48.0

48.0

50

100

150

200

250

5.4

16.2

21.0

23.9

25.3

571/17

1114/28

1573/34

2004/37

2430/39

692/13

1325/26

1886/33

2412/37

2931/39

812/11

1547/24

2209/30

2846/34

3457/36

*CLIMB BEGINS AT SL.

**CLIMB/CRUISE/DESCENT.

Figure P13.(Sheet 2)

T.O. GR1F16CJ1CL2

Change 11P37/(P38 blank)/PW

1F-16X-1CL-1-0002X

Ambient Air Temperature

ALTITUDE

1000 FT

STD TEMP

C

F

SL

5

10

15

20

25

30

35

40

45

50

55

60

15

5

-5

-15

-25

-35

-44

-54

-56

-56

-56

-56

-56

59

41

23

6

-12

-30

-48

-66

-70

-70

-70

-70

-70

F = (9/5 C) + 32

C = 5/9( F - 32 )

Figure P14.

     P37/PW/(P38/PW blank)

T.O. GR1F16CJ1CL2

P1/PW/CFT

SECTION P/PW/CFT

PERFORMANCE DATA

F100PW229 with Conformal Fuel Tanks

TABLE OF CONTENTS

Page

TAKEOFF FACTOR

P2/PW/CFT

. . . . . . . . . . . . . . . . . . . . 

TAKEOFF SPEED AND DISTANCE

P4/PW/CFT

. . . . . 

ACCELERATION CHECK SPEED

P6/PW/CFT

. . . . . . . . 

GROUND VEHICLE FRICTION 

READINGTORCR 

CONVERSION

P7/PW/CFT

. . . . . . . . . . . . . . . . . . . . . 

REFUSAL SPEED

P8/PW/CFT

. . . . . . . . . . . . . . . . . . . . . 

REFUSAL SPEED WITH 

DRAG CHUTE

P12/PW/CFT

. . . . . . . . . . . . . . . . . . . . 

LANDING DENSITY FACTOR

P16/PW/CFT

. . . . . . . . . 

APPROACH SPEEDS

P17/PW/CFT

. . . . . . . . . . . . . . . . . 

SHORT FIELD LANDING 

DISTANCE

P18/PW/CFT

. . . . . . . . . . . . . . . . . . . . . . . . 

SHORT FIELD LANDING

DISTANCE SEC

P20/PW/CFT

. . . . . . . . . . . . . . . . . 

SHORT FIELD LANDING DISTANCE 

WITH DRAG CHUTE

P21/PW/CFT

. . . . . . . . . . . . . . 

SHORT FIELD LANDING DISTANCE-

SEC WITH DRAG CHUTE

P23/PW/CFT

. . . . . . . . . . 

CLIMB/OPTIMUM CRUISE

P25/PW/CFT

. . . . . . . . . . . 

DIVERSION DECISION

DIVERT

P29/PW/CFT

. . . . . . . . . . . . . . . . . . . . . . . . . . 

DIVERSION DECISION

LOITER

P32/PW/CFT

. . . . . . . . . . . . . . . . . . . . . . . . . . . 

BEST CRUISE ALTITUDE FOR SHORT

RANGE MISSION MAXIMUM

RANGE DESCENT

P35/PW/CFT

. . . . . . . . . . . . . . . . . 

AMBIENT AIR TEMPERATURE

P37/PW/CFT

. . . . . . . . 

T.O. GR1F16CJ1CL2

P2/PW/CFT

GR1F-16CJ-1CL-1-2004X37

DATA BASIS FLT TEST

ENGINE F100-PW-229

Takeoff Factor

Figure P1.

T.O. GR1F16CJ1CL2

P4Change 4

GR1F-16CJ-1CL-1-2005X37

Takeoff Speed and Distance

DATA BASIS  ESTIMATED ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES

TUDE

CG = 35% MAC

NOTES:

Refer to sheet 2.

ZERO ROLL TRIM

ALL TEMPERATURES

ALL ALTITUDES

10 DEGREES PITCH ATTI-

Figure P2.(Sheet 1)

(P3/PW/CFT blank)/P4/PW/CFT

T.O. GR1F16CJ1CL2

P5/PW/CFT

Takeoff Speed and Distance

DATA BASIS ESTIMATED

ENGINEF100PW229

CONFIGURATION:

CONDITIONS:

D

ALL DRAG INDEXES

D

CG=35% MAC

D

ZERO ROLL TRIM

D

ALL ALTITUDES

D

ALL TEMPERATURES

D

10 DEGREES PITCH ATTI

TUDE

NOTES:

D

ROTATE AT 10 KIAS (NONAB) OR 15 KIAS (AB) LESS THAN

TAKEOFF SPEED.

D

COMPUTE % INCREASE/DECREASE CHANGES INDIVIDUAL

LY.

D

INCREASE TAKEOFF SPEED 8% AND DISTANCE 18% FOR

AN 8

_

 PITCH ATTITUDE ROTATION.

D

INCREASE/DECREASE TAKEOFF SPEED 0.8 KIAS FOR EACH

1% FORWARD/AFT OF 35% MAC.

D

INCREASE/DECREASE DISTANCE 1% FOR EACH 1% FOR

WARD/AFT OF 35% MAC.

D

INCREASE DISTANCE 2% PER 100 DRAG INDEX.

D

INCREASE DISTANCE 4% PER 1% UPSLOPE.

D

DECREASE DISTANCE 3.5% PER 1% DOWNSLOPE.

D

INCREASE DISTANCE 11% PER 10 KTS TAILWIND.

D

DECREASE DISTANCE 10% PER 10 KTS HEADWIND.

D

FOR TAKEOFF SPEED CORRECTION WITH ROLL TRIM OTH

ER THAN ZERO, REFER TO TAKEOFF ROLL TRIM WITH

ASYMMETRIC STORES, FIGURE N1, PAGE N8.

Figure P2.(Sheet 2)

T.O. GR1F16CJ1CL2

P6/PW/CFT

GR1F-16CJ-1CL-1-2006X37

DATA BASIS ESTIMATED

ENGINE F100-PW-229

NOTES:

COMPUTE % INCREASE/DECREASE CHANGES

INDIVIDUALLY.

DECREASE SPEED 1% PER 100 DRAG INDEX.

INCREASE SPEED 7.6 KIAS PER 10 KTS HEADWIND.

DECREASE SPEED 7.7 KIAS PER 10 KTS TAILWIND.

INCREASE SPEED 3.6% PER 1% DOWNHILL SLOPE.

DECREASE SPEED 3.8% PER 1% UPHILL SLOPE.

Acceleration Check Speed

ACCELERA

TION CHECK SPEED   KIAS

6

5

4

3

2

1 50 45 40 35 30 25 20

TAKEOFF FACTOR

GW   1000 POUNDS

40

60

80

100

120

140

160

180

BASELINE

Figure P3.

T.O. GR1F16CJ1CL2

P7/PW/CFT

1F-16X-1CL-1-0005X

Ground Vehicle Friction Reading

Conversion

NOTES:

IN MANY AREAS, GROUND VEHICLE FRICTION READING

IS THE ONLY AVAILABLE MEASURE FOR RUNWAY

BRAKING ACTION.
NORMALLY THE GROUND VEHICLE FRICTION READING,

ALSO REFERRED TO AS BRAKING ACTION COEFFICIENT,

IS GIVEN AS WHOLE NUMBERS, NOT AS DECIMALS

(I.E., 40 INSTEAD OF 0.40).

GROUND VEHICLE FRICTION READING

RCR/BRAKING ACTION LEVEL

26

24

22

20

18

16

14

12

10

8

6

4

2

0

0.80

0.70

0.60

0.50

0.40

0.30

0.20

0.10

0

MEDIUM

MEDIUM TO POOR

MEDIUM TO GOOD

POOR

GOOD

RCR

To

Figure P4.

T.O. GR1F16CJ1CL2

P8/PW/CFT

Refusal Speed

DATA BASIS ESTIMATED

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES
SPEEDBRAKES   OPEN

GW = 32,000 LB

IDLE SELECTED AT
REFUSAL SPEED
MAX EFFORT BRAKING
DRY CONCRETE (RCR = 23)

NOTES:

COMPUTE % INCREASE/DECREASE CHANGES INDIVIDUALLY.

FOR RCR = 16 (DRY) DECREASE NON-AB/AB REFUSAL SPEED

INCREASE/DECREASE REFUSAL SPEED 1.1%/0.9% WITH

GR1F-16CJ-1CL-1-2008X37

INCREASE/DECREASE REFUSAL SPEED 5/5 KIAS WITH NON-AB

BY 4/5 KIAS.

NON-AB AND 0.7%/0.7% WITH AB PER 1000 LB LESS/

ADDITIONAL GW.

AND 6/6 KIAS WITH AB PER 5 KTS HEADWIND/TAILWIND.

INCREASE/DECREASE REFUSAL SPEED 0.5/1.0 KIAS WITH

NON-AB AND 1.5/2.0 KIAS WITH AB PER 1% UPSLOPE/

DOWNSLOPE.

Figure P5.(Sheet 1)

T.O. GR1F16CJ1CL2

P9/PW/CFT

Refusal Speed

DATA BASIS ESTIMATED

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES
SPEEDBRAKES   OPEN

GW = 32,000 LB

IDLE SELECTED AT
REFUSAL SPEED
MAX EFFORT BRAKING

WET CONCRETE (RCR = 18)

NOTES:

COMPUTE % INCREASE/DECREASE CHANGES INDIVIDUALLY.

FOR RCR = 12 (WET) DECREASE NON-AB/AB REFUSAL SPEED

INCREASE/DECREASE REFUSAL SPEED 0.6%/0.4% WITH

GR1F-16CJ-1CL-1-2009X37

INCREASE/DECREASE REFUSAL SPEED 6/7 KIAS WITH NON-AB

BY 9/10 KIAS.

NON-AB AND 0.2%/0.2% WITH AB PER 1000 LB LESS/

ADDITIONAL GW.

AND 7/8 KIAS WITH AB PER 5 KTS HEADWIND/TAILWIND.

INCREASE/DECREASE REFUSAL SPEED 2.5/4.5 KIAS WITH

NON-AB AND 4.0/5.5 KIAS WITH AB PER 1% UPSLOPE/

DOWNSLOPE.

Figure P5.(Sheet 2)

T.O. GR1F16CJ1CL2

P10/PW/CFT

Refusal Speed

DATA BASIS ESTIMATED

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES
SPEEDBRAKES   OPEN

GW = 32,000 LB

IDLE SELECTED AT
REFUSAL SPEED
MAX EFFORT BRAKING

SNOW (RCR = 8)

NOTES:

COMPUTE % INCREASE/DECREASE CHANGES INDIVIDUALLY.

INCREASE/DECREASE REFUSAL SPEED 0.6%/0.5% WITH

GR1F-16CJ-1CL-1-2010X37

INCREASE/DECREASE REFUSAL SPEED 6/6.5 KIAS WITH NON-AB

NON-AB AND 0.1%/0.2% WITH AB PER 1000 LB LESS/

ADDITIONAL GW.

AND 7/7 KIAS WITH AB PER 5 KTS HEADWIND/TAILWIND.

INCREASE/DECREASE REFUSAL SPEED 2.5/4.5 KIAS WITH

NON-AB AND 4/6 KIAS WITH AB PER 1% UPSLOPE/

DOWNSLOPE.

Figure P5.(Sheet 3)

T.O. GR1F16CJ1CL2

P11/PW/CFT

Refusal Speed

DATA BASIS ESTIMATED

ENGINE F100-PW-229

CONFIGURATION:

CONDITIONS:

ALL DRAG INDEXES
SPEEDBRAKES   OPEN

GW = 32,000 LB

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

NOTES:

COMPUTE % INCREASE/DECREASE CHANGES INDIVIDUALLY.

DECREASE/INCREASE REFUSAL SPEED 0.0%/0.2% WITH

GR1F-16CJ-1CL-1-2011X37

INCREASE/DECREASE REFUSAL SPEED 6/6.5 KIAS WITH NON-AB

NON-AB AND 0.7%/0.2% WITH AB PER 1000 LB LESS/

ADDITIONAL GW.

AND 7/7 KIAS WITH AB PER 5 KTS HEADWIND/TAILWIND.

INCREASE/DECREASE REFUSAL SPEED 2.5/4.5 KIAS WITH

NON-AB AND 4/6 KIAS WITH AB PER 1% UPSLOPE/

DOWNSLOPE.

Figure P5.(Sheet 4)

T.O. GR1F16CJ1CL2

P12/PW/CFT

Refusal Speed With Drag Chute

GR1F-16CJ-1CL-1-2012X37

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
DRY CONCRETE (RCR = 23)

NOTES:

COMPUTE % INCREASE/DECREASE CHANGES INDIVIDUALLY.

FOR RCR = 16 (DRY) DECREASE NONAB/AB DRY RUNWAY

INCREASE/DECREASE REFUSAL SPEED 1.8%/1.1% WITH

INCREASE/DECREASE REFUSAL SPEED 6/6 KIAS WITH NONAB

REFUSAL SPEED BY 2.5/3.5 KIAS.

NON-AB AND 1.7%/1.1% WITH AB PER 1000 LB LESS/

ADDITIONAL GW.

AND 7/7 KIAS WITH AB PER 5 KTS HEADWIND/TAILWIND.

DECREASE/INCREASE REFUSAL SPEED 1/0.5 KIAS WITH

NON-AB AND INCREASE/DECREASE REFUSAL SPEED 0.5/0.5

KIAS WITH AB PER 1% UPSLOPE/DOWNSLOPE.

GW = 32,000 LB

Figure P6. (Sheet 1)