Content .. 81 82 83 84 ..

F16C/D. FLIGHT MANUAL (2002) - page 83

T.O. GR1F16CJ11

C460Change 7

Diversion Decision Loiter

DATA BASIS ESTIMATED

ENGINE F100PW229/CFT

CONDITIONS:

MIL CLIMB AT 433 KIAS OR OPTIMUM

ALTITUDE MACH NUMBER, WHICHEVER IS LESS

DESCEND AT IDLE, 221 KIAS

STANDARD DAY

NO FUEL RESERVE

ZERO WIND

ALL DESCENTS ARE TO SEA LEVEL

DRAG INDEX = 55

IF YOU ARE AT SEA LEVEL

FUEL ON

REMAIN

AT SEA LEVEL

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT SEA LEVEL

FROM

FUEL USED

BOARD

TOTAL LOITER

TIME MIN

ALT/MACH

TOTAL TIME

MIN

FROM

OPT ALT

FUEL USED

IN DESCENT

200

400

0.0K/0.32

600

5.0K/0.35

800

0.32M

20.0K/0.47

222

1000

30.0K/0.55

285

1500

35.0K/0.67

320

2000

35.0K/0.67

320

IF YOU ARE AT 5000 FEET

FUEL ON

REMAIN

AT 5000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 5000 FT

FROM

FUEL USED

BOARD

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

MIN

FROM

OPT ALT

FUEL USED

IN DESCENT

200

400

600

10.0K/0.39

145

800

0.36M

20.0K/0.47

222

1000

35.0K/0.67

320

1500

35.0K/0.67

320

2000

35.0K/0.67

320

START DESCENT AT 12 NM. 84 LB FUEL USED IN DESCENT.

IF YOU ARE AT 10,000 FEET

FUEL ON

REMAIN

AT 10 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 10,000 FT

FROM

FUEL USED

BOARD

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

MIN

FROM

OPT ALT

FUEL USED

IN DESCENT

200

400

600

15.0K/0.43

188

800

0.39M

25.0K/0.51

253

1000

35.0K/0.67

320

1500

35.0K/0.67

320

2000

35.0K/0.67

320

START DESCENT AT 24 NM. 145 LB FUEL USED IN DESCENT.

NOTES:

LOITER TIME AT CONSTANT ALTITUDE BASED ON 10 NM HOLDING PATTERN WITH 30DEGREE BANK

TURNS.

ADD 0.5 MIN TO LOITER TIME FOR EACH 1000 FT OF DESTINATION ELEVATION.

SUBTRACT 2.3 NM FROM DESCENT DISTANCE FOR EACH 1000 FT OF DESTINATION ELEVATION.

TOTAL LOITER TIME AT CURRENT ALTITUDE INCLUDES LOITER AND DESCENT, AND TOTAL TIME AT

OPTIMUM ALTITUDE INCLUDES CLIMB, LOITER, AND DESCENT.

Figure C44.(Sheet 3)

T.O. GR1F16CJ11

Change 7C461

Diversion Decision Loiter

DATA BASIS ESTIMATED

ENGINE F100PW229/CFT

CONDITIONS:

MIL CLIMB AT 433 KIAS OR OPTIMUM

ALTITUDE MACH NUMBER, WHICHEVER IS LESS

DESCEND AT IDLE, 221 KIAS

STANDARD DAY

NO FUEL RESERVE

ZERO WIND

ALL DESCENTS ARE TO SEA LEVEL

DRAG INDEX = 55

IF YOU ARE AT 20,000 FEET

FUEL ON

REMAIN

AT 20 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 20,000 FT

FROM

FUEL USED

BOARD

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

MIN

FROM

OPT ALT

FUEL USED

IN DESCENT

200

400

600

20.0K/0.47

222

800

0.48M

30.0K/0.55

285

1000

35.0K/0.67

320

1500

35.0K/0.67

320

2000

35.0K/0.67

320

START DESCENT AT 44 NM. 222 LB FUEL USED IN DESCENT.

IF YOU ARE AT 30,000 FEET

FUEL ON

REMAIN

AT 30 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 30,000 FT

FROM

FUEL USED

BOARD

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

MIN

FROM

OPT ALT

FUEL USED

IN DESCENT

200

400

600

30.0K/0.55

285

800

0.55M

35.0K/0.67

320

1000

35.0K/0.67

320

1500

35.0K/0.67

320

2000

35.0K/0.67

320

START DESCENT AT 65 NM. 285 LB FUEL USED IN DESCENT.

IF YOU ARE AT 40,000 FEET

FUEL ON

REMAIN

AT 40 000 FT

CLIMB TO OPT ALTITUDE

DESCEND

FUEL ON

BOARD

AT 40,000 FT

FROM

FUEL USED

BOARD

TOTAL LOITER

TIME MIN*

ALT/MACH

TOTAL TIME

MIN

FROM

OPT ALT

FUEL USED

IN DESCENT

200

400

600

800

0.75M

40.0K/0.75

356

1000

40.0K/0.75

356

1500

40.0K/0.75

356

2000

40.0K/0.75

356

START DESCENT AT 93 NM. 356 LB FUEL USED IN DESCENT.

NOTES:

LOITER TIME AT CONSTANT ALTITUDE BASED ON 10 NM HOLDING PATTERN WITH 30DEGREE BANK

TURNS.

ADD 0.5 MIN TO LOITER TIME FOR EACH 1000 FT OF DESTINATION ELEVATION.

SUBTRACT 2.3 NM FROM DESCENT DISTANCE FOR EACH 1000 FT OF DESTINATION ELEVATION.

TOTAL LOITER TIME AT CURRENT ALTITUDE INCLUDES LOITER AND DESCENT, AND TOTAL TIME AT

OPTIMUM ALTITUDE INCLUDES CLIMB, LOITER, AND DESCENT.

Figure C44.(Sheet 4)

T.O. GR1F16CJ11

C462Change 7

Best Cruise Altitude for Short Range

Mission Penetration Descent

DATA BASIS ESTIMATED

ENGINE F100PW229/CFT

CONDITIONS:

STANDARD DAY

NO WIND

MIL CLIMB AT SCHEDULED KIAS OR CONSTANT

ALTITUDE OPTIMUM CRUISE MACH NO., WHICHEVER

IS LOWER

CRUISE AT CONSTANT ALTITUDE AT OPTIMUM MACH

DESCEND AT IDLE WITH SPEEDBRAKES OPEN

DESCENT SPEED = CRUISE MACH TO 300 KIAS, THEN

300 KIAS

START CLIMB

GROSS

TOTAL

MISSION

BEST

CRUISE

TOTAL FUEL CONSUMED (LB)/DESCENT RANGE (NM)

GROSS

WEIGHT*

MISSION

RANGE**

CRUISE

ALTITUDE

100

150

200

250

20,000

100

150

200

250

24,400

33,300

41,200

41,300

429/14.3

674/19.5

891/24.8

1086/24.6

1278/24.4

465/13.2

729/18.3

971/23.4

1187/23.2

1401/23.1

498/12.6

787/17.3

1060/22.1

1295/21.9

1530/21.8

531/12.1

846/16.4

1148/20.7

1404/20.6

1658/20.5

560/11.9

902/15.8

1245/19.9

1521/19.7

1794/19.5

587/11.5

958/15.1

1073/19.3

1399/18.9

1716/18.8

24,000

100

150

200

250

20,100

30,500

39,000

39,200

462/14.3

754/21.3

1007/27.2

1234/27.2

1455/26.9

504/13.0

819/19.7

1043/25.4

1209/25.5

1461/25.3

540/12.1

888/18.4

1207/24.3

1488/24.8

1755/24.5

573/11.4

954/17.4

1312/22.9

1613/23.1

1905/22.7

611/10.8

1022/16.5

1424/21.7

1751/21.8

2067/21.5

644/10.4

1088/15.7

1459/21.4

1655/21.8

1865/21.6

28,000

100

150

200

250

17,000

25,800

31,900

34,600

35,200

493/14.2

824/20.7

1098/25.1

1359/26.8

1610/27.2

537/12.8

898/19.1

1206/23.6

1489/25.1

1773/25.3

576/11.9

975/17.8

1321/21.9

1638/23.6

1946/23.7

615/11.2

1054/16.7

1430/20.6

1781/22.2

2112/22.3

656/10.5

1129/15.7

1545/19.5

1928/20.9

2296/21.1

693/9.9

1202/15.0

1656/18.4

2074/19.8

2477/19.9

32,000

100

150

200

250

14,300

22,600

28,800

31,100

33,100

519/13.6

893/20.6

1202/25.6

1500/27.1

1787/28.6

567/12.4

970/18.9

1327/24.0

1648/25.4

1971/26.7

611/11.4

1058/17.8

1452/22.3

1812/23.9

2159/25.1

652/10.6

1143/16.6

1575/20.8

1973/22.4

2350/23.6

696/9.9

1228/15.5

1700/19.7

2142/21.1

2554/22.3

736/9.3

1310/14.7

1815/18.6

2291/19.9

2757/21.0

36,000

100

150

200

250

12,000

20,400

27,000

29,400

30,800

543/13.0

956/20.5

1304/26.2

1636/28.1

1959/29.2

595/11.7

1041/18.8

1437/24.8

1801/26.3

2162/27.2

643/10.8

1135/17.8

1578/23.1

1976/24.9

2366/25.7

686/10.2

1229/16.7

1711/21.7

2151/23.6

2580/24.3

736/9.5

1323/15.6

1851/20.5

2344/22.2

2811/22.9

780/8.9

1413/14.8

1980/19.3

2510/20.8

3028/21.5

40,000

100

150

200

250

9,400

19,300

23,800

27,500

28,900

569/11.4

1019/20.9

1405/25.1

1775/28.3

2133/29.5

624/10.1

1112/19.4

1552/23.7

1953/26.6

2352/27.7

675/9.4

1212/18.1

1701/22.0

2148/25.2

2581/26.2

720/9.0

1312/17.2

1843/20.9

2333/24.0

2810/24.8

775/8.3

1418/16.2

1995/19.8

2541/22.7

3058/23.5

822/7.7

1518/15.5

2133/18.6

2725/21.2

3300/22.0

44,000

100

150

200

250

7,000

17,300

21,300

25,300

26,900

594/10.0

1084/20.1

1509/24.0

1905/28.0

2297/29.3

649/8.8

1183/18.7

1663/22.6

2103/26.2

2539/27.5

705/7.9

1292/17.4

1823/21.0

2315/24.8

2790/26.0

754/7.6

1399/16.6

1977/19.9

2518/23.6

3040/24.8

813/7.0

1513/15.8

2138/19.0

2733/22.5

3305/23.4

863/6.5

1619/15.0

2286/17.9

2934/21.0

3567/22.0

48,000

100

150

200

250

5,300

15,700

21,100

23,600

25,200

617/8.9

1147/19.3

1607/25.0

2036/27.5

2461/28.8

675/7.6

1254/18.0

1769/23.4

2253/25.7

2720/27.4

734/6.9

1373/16.8

1945/22.1

2479/24.5

3003/25.8

787/6.5

1486/16.1

2114/21.0

2701/23.3

3270/24.5

852/6.1

1608/15.4

2283/19.9

2931/22.0

3555/23.3

908/5.6

1719/14.5

2444/19.1

3146/20.9

52,000

100

150

200

250

4,400

14,300

19,500

22,300

23,500

642/8.2

1211/18.5

1703/24.4

2165/26.9

2625/27.9

701/7.1

1325/17.3

1882/22.8

2399/25.4

2904/26.7

765/6.3

1453/16.2

2068/21.5

2645/24.2

3217/25.2

821/5.9

1575/15.4

2248/20.5

2888/23.1

3497/24.1

892/5.5

1704/14.8

2424/19.5

3132/21.8

953/5.2

1822/14.0

2602/18.6

3358/20.7

CLIMB BEGINS AT SL.

CLIMB/CRUISE/DESCENT.

Figure C45.(Sheet 1)

T.O. GR1F16CJ11

Change 7C463/(C464 blank)

Best Cruise Altitude for Short Range

Mission Maximum Range Descent

DATA BASIS ESTIMATED

ENGINE F100PW229/CFT

CONDITIONS:

STANDARD DAY

NO WIND

MIL CLIMB AT SCHEDULED KIAS OR CONSTANT

ALTITUDE OPTIMUM CRUISE MACH NO., WHICHEVER

IS LOWER

CRUISE AT CONSTANT ALTITUDE AT OPTIMUM

MACH

DESCEND AT IDLE WITH SPEEDBRAKES CLOSED

DESCENT INDEX/DESCENT SPEED KIAS =

0/215, 50/220, 100/230

START CLIMB

GROSS

TOTAL

MISSION

BEST

CRUISE

TOTAL FUEL CONSUMED (LB)/DESCENT RANGE (NM)

GROSS

WEIGHT

MISSION

RANGE

CRUISE

ALTITUDE

100

150

200

250

20,000

100

150

200

250

14,600

30,300

35,900

41,600

41,800

401/46.3

670/87.4

895/107.6

1101/132.2

1295/134.0

427/38.7

693/75.1

933/90.9

1158/110.2

1375/111.0

449/32.0

731/61.8

987/74.2

1237/89.5

1473/89.8

475/28.4

779/54.5

1053/65.4

1333/79.1

1589/79.1

504/25.3

828/48.9

1131/58.7

1444/69.9

1721/69.9

534/22.7

875/44.3

1202/53.0

1236/63.4

1582/63.4

24,000

100

150

200

250

15,700

29,400

34,600

36,300

36,700

414/44.6

719/78.4

969/92.5

1199/97.6

1426/99.8

438/39.7

756/69.9

1030/82.9

1281/87.9

1532/89.3

465/34.7

802/61.3

1097/72.5

1380/76.3

1656/77.4

497/31.1

858/55.3

1186/65.6

1489/69.2

1789/70.2

529/28.2

917/50.3

1277/59.9

1600/63.3

1925/64.0

561/25.8

977/46.4

1370/55.0

1721/58.1

2063/58.6

28,000

100

150

200

250

16,800

27,100

32,200

35,000

35,600

432/42.7

776/65.6

1056/76.8

1320/83.6

1570/86.2

467/38.6

823/60.1

1133/71.9

1419/77.8

1704/79.7

489/35.9

878/55.3

1220/65.7

1535/72.0

1845/73.3

522/32.9

941/50.8

1315/60.6

1663/66.3

1994/67.7

559/30.1

1011/47.0

1418/56.3

1801/61.2

2167/62.9

594/27.9

1079/43.8

1521/52.4

1937/57.1

2343/58.0

32,000

100

150

200

250

15,800

24,800

30,000

32,700

34,000

463/37.9

839/55.0

1152/64.8

1449/71.1

1736/74.3

492/34.9

897/51.6

1242/62.1

1570/67.4

1891/70.7

526/32.4

958/48.7

1345/59.2

1695/64.5

2045/67.3

563/30.2

1032/45.6

1453/55.0

1843/60.4

2222/62.7

605/28.3

1110/42.7

1566/51.6

2002/56.6

2409/59.1

642/26.4

1186/40.3

1683/48.4

2152/52.9

2616/55.6

36,000

100

150

200

250

13,700

21,900

28,300

30,500

31,500

493/31.8

905/45.2

1258/55.8

1585/60.6

1907/63.0

527/29.4

972/43.0

1357/54.4

1727/58.4

2085/60.9

567/27.6

1043/41.2

1471/53.3

1864/57.1

2257/59.2

608/25.7

1125/39.2

1595/50.0

2025/54.3

2456/55.8

655/24.3

1213/36.8

1724/47.1

2205/51.5

2660/53.1

695/22.8

1295/35.0

1844/44.9

2369/48.4

2883/50.1

40,000

100

150

200

250

11,700

20,300

26,000

28,400

29,200

523/26.7

973/39.2

1360/48.1

1731/51.7

2084/53.6

564/24.5

1050/37.6

1476/46.9

1883/50.9

2280/52.8

609/23.2

1130/36.5

1602/46.7

2045/50.5

2474/52.1

654/21.5

1219/34.9

1740/44.3

2217/48.3

2697/49.5

704/20.5

1316/33.1

1878/41.9

2410/46.2

2916/47.4

750/19.4

1407/31.7

2009/40.0

2594/43.4

3160/44.9

44,000

100

150

200

250

8,400

18,900

24,100

26,000

27,100

550/21.3

1043/34.5

1468/41.7

1866/44.8

2259/46.2

601/18.7

1131/32.9

1598/40.6

2044/43.6

2476/45.7

652/17.4

1221/32.5

1737/41.1

2223/44.3

2696/46.0

697/16.5

1317/31.2

1887/39.3

2413/42.3

2937/44.0

754/15.5

1422/29.7

2037/37.1

2617/40.8

3182/42.1

804/14.6

1521/28.5

2180/35.7

2817/38.3

3440/40.1

48,000

100

150

200

250

6,300

16,600

21,400

23,800

25,400

572/18.2

1113/29.5

1575/35.8

2005/38.8

2433/40.4

630/15.5

1210/28.1

1724/34.4

2207/37.7

2672/40.2

687/14.1

1312/27.7

1875/34.7

2402/38.6

2925/40.7

739/13.1

1418/26.6

2035/33.3

2615/36.9

3181/39.1

802/12.4

1533/25.5

2197/31.5

2835/35.3

3454/37.5

858/11.5

1640/24.2

2351/30.5

3046/33.5

52,000

100

150

200

250

4,400

14,200

19,800

22,300

23,300

595/15.4

1182/25.1

1677/32.1

2145/34.3

2605/35.3

658/12.8

1289/23.9

1845/30.8

2365/33.6

2867/35.4

722/11.4

1402/23.4

2010/30.8

2583/34.4

3154/35.9

778/10.5

1519/22.4

2184/29.5

2818/33.1

3425/34.6

847/9.8

1643/21.6

2356/28.1

3056/31.3

908/9.1

1758/20.3

2527/27.1

3275/29.9

CLIMB BEGINS AT SL.

CLIMB/CRUISE/DESCENT.

Figure C45.(Sheet 2)

T.O. GR1F16CJ11

C61

PART 5-ENDURANCE

Refer to SUBSONIC CRUISE TABLES, Part 4, for

endurance information.

PART 6-DESCENT

TABLE OF CONTENTS

Page

Maximum Range Descent

C61

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

Penetration Descent

C61

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

Descent With Inoperative Engine

C62

. . . . . . . . . .

LIST OF CHARTS

Figure

Page

Maximum Range Descent-

Idle

C61

C63

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

. . . .

Penetration Descent

C62

C65

. . . . . . .

. . . .

Descent With Inoperative

Engine

C63

C66

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

. . . .

MAXIMUM RANGE DESCENT

Maximum range descent performance data is pres

ented in figure C61. The data is based on a descent

speed which results in maximum distance (range)

being covered during descent. Effects of GW and drag

index are shown in the chart. Descent speed is tabu

lated on the chart.

REFER TO FIGURE C61.

Enter chart on sheet 1 with initial altitude (A), and

proceed upward to intercept appropriate drag index

line (B), and then proceed to the right to the baseline.

Note this point on the baseline. Enter GW block at (C),

proceed to the right to intercept the appropriate drag

index line (B), and proceed downward to intercept a

line (D) which follows the guidelines and intercepts

the point previously noted on the baseline. Continue

to the right to read range (E). Repeat this process on

sheet 2 in the same manner to obtain the fuel con

sumed (F) and time (G). If final altitude is above sea

level, repeat the above process, using final altitude in

place of initial altitude. The difference between the

resulting values is then range, fuel, and time to

descend from initial to final altitude. Obtain descent

speed from the table on the chart.

SAMPLE PROBLEM.

A. Initial altitude

= 30,000 feet

B. Drag index

= 50

C. GW

= 35,000 pounds

D. Intersection point

E. Range

= 50 nm

F. Fuel consumed

= 214 pounds

G. Time

= 11.0 minutes

Descent speed

= 220 KIAS

The above data is for a descent to sea level. If the

descent was stopped at 5000 feet:

Range

= 50-9 = 41 nm

Fuel consumed

= 214-60 = 154 pounds

Time

= 11.0-2.3 = 8.7 minutes

PENETRATION DESCENT

Fuel consumed, distance, and time to execute a

penetration descent are shown in figure C62. The

data is based on idle rpm, 300 KIAS, and speedbrakes

open. Effects of GW and drag index are shown on the

chart.

REFER TO FIGURE C62.

Enter chart with initial altitude (A), and proceed

upward to intercept appropriate drag index line in the

time, range, and fuel blocks (B), and then proceed to

the right to GW baseline and follow guidelines to GW

(C). Continue to the right to read fuel consumed (D),

range (E), and time (F). If final altitude is above sea

level, repeat the above process using final altitude in

place of initial altitude. The difference between the

resulting values is then fuel, range, and time to

descend from initial to final altitude.

Change 7C51/C61

T.O. GR1F16CJ11

C62Change 7

SAMPLE PROBLEM.

A. Initial altitude

= 30,000 feet

B. Drag index

= 100

C. GW

= 35,000 pounds

D. Fuel consumed

= 82 pounds

E. Range

= 25 nm

F. Time

= 4.2 minutes

The above data is for a descent to sea level. If the

descent was stopped at 5000 feet:

Fuel consumed

= 82-22 = 60 pounds

Range

= 25-4 = 21 nm

Time

= 4.2-0.8 = 3.4 minutes

DESCENT WITH INOPERATIVE ENGINE

Figure C63 contains time and distance data for a

descent with an inoperative engine. The data is

presented as a function of descent airspeed for

descents from various initial altitudes to sea level.

Minimum EPU operating time is shown.

The chart is intended to be used to estimate the time

available for engine airstart attempts once the air

craft has been maneuvered into the airstart envelope

and may also be used to obtain glide distance with the

engine inoperative.

REFER TO FIGURE C63.

Enter the chart with airspeed (A), proceed upward to

the appropriate GW/altitude line (B), and then to the

left to read time (C) and distance (D). To determine

time and distance available to descend to another

altitude, repeat the above steps for the final altitude

and take the difference between the sets of data.

SAMPLE PROBLEM.

A. Descent airspeed

= 250 KIAS

B. GW/altitude

20,000 pounds/

30,000 feet

C. Time (to sea level) = 8.4 minutes

D. Distance (to sea

level)

= 42.9 nm

If the descent was stopped at 5000 feet:

Time

= 8.4-1.6 = 6.8 minutes

Distance

= 42.9-7.0 = 35.9 nm

T.O. GR1F16CJ11

Change 7C63

1F-16CJ-1-1-1038X37

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229/CFT

SPEEDBRAKES CLOSED

STANDARD DAY

Maximum Range Descent IDLE

100

120

140

160

DESCENT SPEED

DRAG INDEX KIAS

100

200

300

400

215

220

230

RANGE NM

BASELINE

100

200

300 400

DRAG INDEX

400

300

200

100

GW 1000 POUNDS

ALTITUDE 1000 FEET

Figure C61.(Sheet 1)

T.O. GR1F16CJ11

C64Change 7

1F-16CJ-1-1-1039X37

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229/CFT

SPEEDBRAKES CLOSED

STANDARD DAY

Maximum Range Descent IDLE

DESCENT SPEED

DRAG INDEX KIAS

100

200

300

400

215

220

230

ALTITUDE 1000 FEET

TIME MINUTES

GW 1000 POUNDS

BASELINE

FUEL 100 POUNDS

BASELINE

100

200

300 400

DRAG INDEX

400

300

200

100

200

300

400

100

200

300

400

Figure C61.(Sheet 2)

T.O. GR1F16CJ11

Change 7C65

100

200

300

400

INITIAL ALTITUDE 1000 FEET

160

1F-16CJ-1-1-1040X37

TIME MINUTES

DIST

ANCE NM

FUEL CONSUMED POUNDS

INITIAL GW 1000 POUNDS

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229/CFT

SPEEDBRAKES OPEN

Penetration Descent

IDLE
DESCENT SPEED = CRUISE MACH

TO 300 KIAS, THEN 300 KIAS
STANDARD DAY

BASELINE

120

100

200

300

400

100

200

300

400

Figure C62.

T.O. GR1F16CJ11

C66Change 7

1F-16CJ-1-1-1041X37

160

180

200

220

240

260

280

300

DIST

ANCE TO DESCEND TO SEA LEVEL NM

TIME TO DESCEND TO SEA LEVEL MINUTES

AIRSPEED KIAS

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229/CFT

DRAG INDEX = 0

STANDARD DAY

Descent With Inoperative Engine

WINDMILLING ENGINE OR LOCKED ROTOR

NO WIND

NOTE: REDUCE TIME AND DISTANCE 1% FOR EACH 10-UNIT INCREASE IN DRAG INDEX.

150

170

190

210

230

270

290

250

Figure C63.

T.O. GR1F16CJ11

Change 7C71

PART 7-LANDING

TABLE OF CONTENTS

Page

Definition of Terms

C71

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

Landing Speed

C71

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

Short Field Landing

C71

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

LIST OF CHARTS

Figure

Page

Landing Speed

C71

C73

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

. . . .

Short Field Landing

Distance

(Uncorrected)

C72

C74

. . . . . . . . . . .

. . . .

Short Field Landing

Distance

(Corrected)

C72

C75

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

. . . .

Short Field Landing

Distance-SEC

(Corrected)

C72

C76

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

. . . .

Short Field Landing

Distance - With Drag

Chute (Uncorrected)

C72

C77

. . . . .

. . . .

Short Field Landing

Distance - With Drag

Chute (Corrected)

C72

C78

. . . . . . .

. . . .

Short Field Landing

Distance - SEC With

Drag Chute (Corrected)

C72

C79

. . .

. . . .

DEFINITION OF TERMS

Aerodynamic braking (twopoint attitude)-Use of

speedbrakes and maximum of 13 degrees AOA until

deceleration to 100 KIAS.

Maximum effort braking-A single continuous wheel

brake application using maximum pedal pressure

(antiskid on) in conjunction with twopoint aerody

namic braking (consistent with maintaining direc

tional control). When wheel brakes become effective,

the aircraft will automatically rotate to the three

point attitude. After the nose tire is on the runway,

maintain full aft stick short of nose tire liftoff and

open speedbrakes fully. On a dry runway, the nose

lowers soon after wheel brakes are applied.

LESS

b2t

On a wet or icy runway, wheel brakes are not applied

until deceleration to 100 KIAS to allow wheel spinup

and proper antiskid operation.

b2t

On a wet or icy

runway, apply brakes at any landing speed. Short

Field Landing Distance charts are based on brakes

applied at 100 KIAS.

Use drag chute immediately after touchdown in con

junction with proper wheel braking and allow aircraft

to rotate to the three-point attitude as the drag chute

opens. At touchdown speeds above 170 KIAS use

maximum effort braking and delay drag chute de

ployment (and rotation to threepoint attitude) until

deceleration to 170 KIAS.

LANDING SPEED

Final approach and touchdown airspeeds are given in

figure C71. Both airspeeds are based on 13 degrees

AOA, matching the AOA indexer on speed indication.

SAMPLE PROBLEM.

A. GW

= 20,000 pounds

B. Touchdown speed

= 125 KIAS

C. Final approach

speed

= 136 KIAS

SHORT FIELD LANDING

Ground roll distance for minimum distance landing is

given in figure C72 (sheets 1 through 6).

Data for measured runway condition readings (RCR)

not provided on charts can be obtained by interpola

tion. For wet runways, interpolate between RCR 18

(WET), RCR 12 (WET), and RCR 10 (WET). For run

ways with no liquid water present, interpolate

between RCR 23 (DRY CONCRETE), RCR 16 (DRY),

RCR 8 (SNOW), and RCR 4 (ICY). If RCR is unknown

and runway is wet, use RCR 18 (WET) for wet con

crete and RCR 12 (WET) for wet asphalt.

REFER TO FIGURE C72.

Enter sheet 1 with pressure altitude (A), proceed to

the right to temperature (B), down to GW (C), and

finally to the right and read uncorrected ground roll

distance (D). Enter sheets 2 and 3 with uncorrected

ground roll distance (D). Continue to the right to the

reported RCR (E) or (I), proceed down to baseline and

follow guidelines to wind (F), and then proceed down

to baseline and follow guidelines to slope (G). Finally,

proceed down to read corrected ground roll distance

(H) or (J).

Short field landing with drag chute is shown on sheets

4 through 6.

T.O. GR1F16CJ11

C72Change 7

SAMPLE PROBLEM (SHEET 1).

A. Altitude

= 2000 feet

B. Temperature

= 40

C. GW

= 28,000 pounds

D. Uncorrected ground

roll distance:

PRI

= 3929 feet

SEC (3929

1.105) = 4342 feet

SAMPLE PROBLEM (SHEET 2).

D. Uncorrected ground

roll distance (PRI)

= 3929 feet

E. RCR

= 16

F. Wind

= 10 knots (headwind)

G. Slope

= 1 percent (uphill)

H. Corrected ground roll

distance

= 3398 feet

I. RCR

= 4

J. Corrected ground roll

distance

= 8309 feet

SAMPLE PROBLEM (SHEET 3).

D. Uncorrected ground

roll distance (SEC)

= 4342 feet

E. RCR

= 16

F. Wind

= 10 knots (headwind)

G. Slope

= 1 percent (uphill)

H. Corrected ground roll

distance

= 3732 feet

I. RCR

= 8

J. Corrected ground roll

distance

= 6672 feet

SAMPLE PROBLEM (SHEET 4).

A. Altitude

= 2000 feet

B. Temperature

= 40

C. GW

= 28,000 pounds

D. Uncorrected ground

roll distance:

PRI

= 2514 feet

SEC (2514

1.06) = 2665 feet

SAMPLE PROBLEM (SHEET 5).

D. Uncorrected ground

roll distance (PRI)

= 2514 feet

E. RCR

= 16

F. Wind

= 10 knots (headwind)

G. Slope

= 1 percent (uphill)

H. Corrected ground roll

distance

= 2117 feet

I. RCR

= 4

J. Corrected ground roll

distance

= 3883 feet

SAMPLE PROBLEM (SHEET 6).

D. Uncorrected ground

roll distance (SEC)

= 2665 feet

E. RCR

= 16

F. Wind

= 10 knots (headwind)

G. Slope

= 1 percent (uphill)

H. Corrected ground roll

distance

= 2260 feet

I. RCR

= 4

J. Corrected ground roll

distance

= 5183 feet

T.O. GR1F16CJ11

Change 7C73

1F-16CJ-1-1-0015X37

Landing Speed

DATA BASIS ESTIMATED

CONDITIONS:

CONFIGURATION:

ALL DRAG INDEXES

ALL TEMPERATURES
ALL ALTITUDES

13 DEGREES AOA (INDEXER ON SPEED)

120

GW 1000 POUNDS

AIRSPEED KIAS

THE BASELINE AIRSPEEDS ARE BASED ON THE BASIC OPERATING WEIGHT PLUS FULL AMMO.

ACTUAL APPROACH AIRSPEED AT 13 DEGREES AOA MAY DIFFER BY +/-5 KNOTS DUE TO

VARIATIONS IN AIRCRAFT CG.

NOTE:

140

160

180

200

220

Figure C71.

T.O. GR1F16CJ11

C74Change 7

1F-16CJ-1-1-1043X37

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229/CFT

TOUCHDOWN AT 13 DEGREES AOA

Short Field Landing Distance (Uncorrected)

ZERO WIND AND SLOPE

IDLE SELECTED AT TOUCHDOWN

MAX EFFORT BRAKING
DRY CONCRETE RUNWAY

ALL DRAG INDEXES
SPEEDBRAKES OPEN

1000

2000

3000

4000

5000

6000

7000

8000

UNCORRECTED GROUND ROLL 1000 FEET

TITUDE FEET

NOTE: DURING SEC, INCREASE UNCORRECTED GROUND ROLL

DISTANCE BY 10.5/10 PERCENT WHEN BELOW/ABOVE

MAXIMUM BRAKE LIMIT LINE. USE SHEET 3 TO

DETERMINE CORRECTED GROUND ROLL DISTANCE.

MLG TIRE LIMIT SPEED

(225 KTS NO WIND)

NLG TIRE LIMIT SPEED

(217 KTS NO WIND)

Figure C72.(Sheet 1)

T.O. GR1F16CJ11

Change 7C75

1F-16CJ-1-1-1044X37

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229/CFT

TOUCHDOWN AT 13 DEGREES AOA

Short Field Landing Distance (Corrected)

ALL DRAG INDEXES
SPEEDBRAKES OPEN

IDLE SELECTED AT TOUCHDOWN
MAX EFFORT BRAKING

ENTER CHART WITH UNCORRECTED GROUND
ROLL DISTANCE FROM SHEET 1

CORRECTED GROUND ROLL DISTANCE 1000 FEET

UNCORRECTED GROUND ROLL DIST

ANCE 1000 FEET

BASELINE

2
3

WIND

KNOTS

SLOPE

Figure C72.(Sheet 2)

T.O. GR1F16CJ11

C76Change 7

1F-16CJ-1-1-1045X37

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F100-PW-229/CFT

TOUCHDOWN AT 13 DEGREES AOA

Short Field Landing Distance SEC

ALL DRAG INDEXES
SPEEDBRAKES OPEN

IDLE SELECTED AT TOUCHDOWN
MAX EFFORT BRAKING
ENTER CHART WITH UNCORRECTED GROUND
ROLL DISTANCE

CORRECTED GROUND ROLL DISTANCE 1000 FEET

UNCORRECTED GROUND ROLL DIST

ANCE 1000 FEET

BASELINE

ON AN ICY RUNWAY

(RCR = 4) WITH SEC,

THE STOPPING DISTANCE

WITH ZERO HEADWIND

EXCEEDS 14,000 FEET.

(Corrected)

2
3

WIND

KNOTS

SLOPE

Figure C72.(Sheet 3)

Content .. 81 82 83 84 ..

F16C/D. FLIGHT MANUAL (2002) - page 83

F16C/D. FLIGHT MANUAL (2002) - page 83