Content .. 70 71 72 73 ..

F16C/D. FLIGHT MANUAL (2002) - page 72

T.O. GR1F16CJ11

B462Change 3

Best Cruise Altitude for Short Range

Mission Penetration Descent

DATA BASIS FLIGHT TEST

ENGINE F110GE129

CONDITIONS:

STANDARD DAY

NO WIND

MIL CLIMB AT SCHEDULE 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

24,200

30,800

36,200

37,500

42,000

421/12.4

654/16.2

862/19.4

1078/20.1

1239/23.1

451/11.6

712/15.2

944/18.2

1168/19.0

1401/21.4

479/11.0

769/14.5

1029/17.1

1274/17.8

1519/20.6

508/10.5

821/13.9

1114/16.3

1381/17.1

1648/19.5

537/10.3

874/13.3

1189/15.8

1484/16.3

1765/18.8

565/10.1

927/12.6

1256/15.4

1572/16.0

1876/18.0

24,000

100

150

200

250

19,600

29,200

33,400

35,800

37,500

456/11.7

726/18.3

972/20.9

1204/22.8

1411/24.1

488/10.9

795/17.0

1064/19.6

1320/21.0

1594/22.0

517/10.3

860/16.0

1159/18.4

1440/19.8

1726/20.7

549/9.8

923/15.1

1258/17.4

1564/18.6

1874/19.5

585/9.3

987/14.4

1352/16.5

1687/17.6

2021/18.5

617/9.0

1048/13.7

1437/15.9

1804/16.8

2146/17.7

28,000

100

150

200

250

16,900

27,000

30,900

33,500

36,000

482/11.9

795/19.5

1080/22.3

1333/25.1

1560/26.6

520/11.0

875/18.1

1181/20.7

1480/22.3

1754/24.3

552/10.4

946/17.0

1286/19.4

1617/21.0

1921/22.6

589/9.7

1018/16.0

1394/18.3

1756/19.8

2094/21.3

628/9.2

1094/15.1

1499/17.4

1892/18.8

2259/20.1

664/8.8

1162/14.4

1599/16.5

2017/17.8

2430/19.1

32,000

100

150

200

250

14,200

21,600

28,100

33,600

33,700

506/11.4

862/17.5

1177/22.9

1440/28.1

1720/27.9

548/10.5

947/16.2

1292/21.0

1623/25.8

1940/25.6

585/9.9

1031/15.1

1415/19.7

1781/24.0

2131/23.7

625/9.2

1106/14.1

1534/18.6

1935/22.7

2316/22.4

668/8.6

1182/13.3

1649/17.6

2090/21.4

2501/21.1

709/8.1

1255/12.6

1757/16.8

2283/20.1

2724/19.9

36,000

100

150

200

250

11,300

20,000

25,900

30,000

527/10.4

922/18.0

1286/23.3

1574/27.8

1890/27.6

574/9.5

1016/16.6

1403/21.3

1771/25.3

2131/25.0

615/8.9

1105/15.5

1537/20.2

1940/23.7

2335/23.4

658/8.3

1187/14.5

1669/19.1

2116/22.3

2548/22.0

707/7.7

1274/13.7

1798/18.0

2277/20.8

2741/20.5

751/7.2

1356/12.9

1912/17.1

2424/19.8

2920/19.5

40,000

100

150

200

250

9,500

18,900

25,100

28,000

546/10.0

980/18.5

1368/25.2

1698/27.9

2047/27.8

597/9.0

1084/17.1

1515/22.7

1913/25.7

2309/25.4

646/8.2

1179/16.1

1660/21.3

2100/24.1

2536/23.8

693/7.8

1270/15.1

1802/20.3

2292/22.8

2768/22.5

745/7.2

1370/14.3

1939/19.2

2469/21.2

2983/21.0

793/6.8

1460/13.4

2072/18.1

2629/20.1

3177/19.9

CLIMB BEGINS AT SL.

CLIMB/CRUISE/DESCENT.

Figure B45.(Sheet 1)

T.O. GR1F16CJ11

Change 3B463/(B464 blank)

Best Cruise Altitude for Short Range

Mission Maximum Range Descent

DATA BASIS FLIGHT TEST

ENGINE F110GE129

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

DRAG 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

22,900

32,900

37,400

42,000

374/42.5

606/69.1

824/86.5

1004/111.4

1194/112.0

387/38.5

652/60.2

880/72.5

1107/94.7

1323/94.8

411/33.3

701/50.5

952/60.9

1198/73.7

1435/73.2

438/30.3

750/45.5

1031/54.6

1301/65.6

1559/65.0

467/27.7

803/41.6

1110/49.6

1397/58.6

1675/58.2

495/25.5

852/38.3

1179/45.2

1490/53.5

1784/53.1

24,000

100

150

200

250

19,500

30,100

35,200

37,900

398/36.0

666/60.2

909/76.3

1123/86.4

1345/87.1

422/32.9

721/54.1

984/65.7

1251/77.2

1506/76.4

442/30.0

773/48.2

1065/58.3

1350/65.3

1628/65.2

471/27.8

831/44.4

1156/53.7

1466/59.8

1768/59.7

506/25.7

893/41.0

1245/49.9

1584/54.8

1908/54.6

538/23.9

951/38.2

1333/46.0

1689/50.5

2037/50.3

28,000

100

150

200

250

19,900

27,900

32,600

36,000

418/36.7

730/52.8

1008/65.4

1242/74.4

1491/74.8

447/33.9

792/49.2

1096/58.5

1379/67.9

1661/68.2

478/31.0

850/45.0

1187/54.0

1498/61.7

1809/61.8

509/29.1

916/42.2

1285/50.6

1633/57.4

1971/57.3

547/27.6

987/39.6

1388/47.3

1762/53.7

2127/53.7

583/25.9

1051/37.1

1479/44.0

1900/50.1

2293/50.0

32,000

100

150

200

250

17,500

25,700

31,600

33,100

33,900

445/31.5

797/45.9

1093/59.9

1373/62.8

1648/64.6

481/29.1

867/43.6

1212/54.8

1532/58.4

1844/60.5

514/27.3

929/41.0

1309/52.1

1666/55.1

2012/56.8

551/25.7

1004/38.8

1422/49.1

1808/52.0

2185/53.5

592/24.5

1083/36.8

1532/46.0

1953/48.7

2361/50.4

632/23.3

1154/34.6

1633/43.4

2116/45.8

2594/47.1

36,000

100

150

200

250

14,600

22,100

29,700

30,000

475/26.1

865/37.4

1192/52.2

1508/52.9

1825/53.3

516/24.0

947/35.8

1325/48.7

1687/49.5

2046/49.6

555/22.6

1014/34.5

1434/47.1

1832/47.8

2227/47.9

594/21.4

1097/32.5

1561/44.7

1996/45.4

2427/45.4

641/20.3

1183/31.0

1680/42.0

2150/42.6

2615/42.6

682/19.4

1260/29.2

1790/39.9

2290/40.6

2785/40.7

40,000

100

150

200

250

11,800

20,300

28,000

500/22.0

932/32.9

1291/46.3

1641/46.7

1988/47.1

549/19.7

1023/31.7

1440/43.9

1838/44.1

2233/44.2

592/18.5

1100/30.6

1563/42.9

2001/43.1

2436/43.3

637/17.5

1192/29.1

1704/40.9

2183/41.0

2658/41.2

689/16.7

1286/27.6

1834/38.5

2352/38.6

2865/38.8

734/16.0

1370/26.1

1953/36.6

2505/36.9

3052/37.1

CLIMB BEGINS AT SL.

CLIMB/CRUISE/DESCENT.

Figure B45.(Sheet 2)

T.O. GR1F16CJ11

B61

PART 5-ENDURANCE

Refer to SUBSONIC CRUISE TABLES, Part 4, for

endurance information.

PART 6-DESCENT

TABLE OF CONTENTS

Page

Maximum Range Descent

B61

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

Penetration Descent

B61

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

Descent With Inoperative Engine

B62

. . . . . . . . . .

LIST OF CHARTS

Figure

Page

Maximum Range Descent-

Idle

B61

B63

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

. . . .

Penetration Descent

B62

B65

. . . . . . .

. . . .

Descent With Inoperative

Engine

B63

B66

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

. . . .

MAXIMUM RANGE DESCENT

Maximum range descent performance data is pres

ented in figure B61. 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 B61.

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

= 30,000 pounds

D. Intersection point

E. Range

= 46 nm

F. Fuel consumed

= 164 pounds

G. Time

= 10.0 minutes

Descent speed

= 220 KIAS

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

descent was stopped at 5000 feet:

Range

= 46-7 = 39 nm

Fuel consumed

= 165-33 = 132 pounds

Time

= 10.0-1.8 = 8.2 minutes

PENETRATION DESCENT

Fuel consumed, distance, and time to execute a

penetration descent are shown in figure B62. 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 B62.

Enter chart with initial altitude (A), 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 result

ing values is then fuel, range, and time to descend

from initial to final altitude.

Change 3 B51/B61

T.O. GR1F16CJ11

B62Change 3

SAMPLE PROBLEM.

A. Initial altitude

= 30,000 feet

B. Drag index

= 100

C. GW

= 24,000 pounds

D. Fuel consumed

= 57 pounds

E. Range

= 18 nm

F. Time

= 3.0 minutes

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

descent was stopped at 5000 feet:

Fuel consumed

= 57-9 = 48 pounds

Range

= 18-3 = 15 nm

Time

= 3.0-0.5 = 2.5 minutes

DESCENT WITH INOPERATIVE ENGINE

Figure B63 contains time and distance data for a

descent with an inoperative engine. The data is pre

sented 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 aircraft

has been maneuvered into the airstart envelope and

may also be used to obtain glide distance with the

engine inoperative.

REFER TO FIGURE B63.

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) = 8.0 minutes

D. Distance (to sea

level)

= 40.9 nm

If the descent was stopped at 5000 feet:

Time

= 8.0-1.5 = 6.5 minutes

Distance

= 40.9-6.6 = 34.3 nm

T.O. GR1F16CJ11

Change 3B63

1F-16CJ-1-1-4038A

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

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 B61.(Sheet 1)

T.O. GR1F16CJ11

B64Change 3

1F-16CJ-1-1-4039A

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

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

DRAG INDEX

100

200

300

400

DRAG INDEX

100

200

300

400

Figure B61.(Sheet 2)

T.O. GR1F16CJ11

Change 3B65

100

200

300

400

INITIAL ALTITUDE 1000 FEET

160

1F-16CJ-1-1-4040A

TIME MINUTES

DIST

ANCE NM

FUEL CONSUMED POUNDS

INITIAL GW 1000 POUNDS

DATA BASIS FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

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 B62.

T.O. GR1F16CJ11

B66Change 3

1F-16CJ-1-1-4041A

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 FLIGHT TEST

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

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.

Figure B63.

T.O. GR1F16CJ11

Change 6B71

PART 7-LANDING

TABLE OF CONTENTS

Page

Definition of Terms

B71

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

Landing Speed

B71

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

Short Field Landing

B71

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

LIST OF CHARTS

Figure

Page

Landing Speed

B71

B73

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

. . . .

Short Field Landing

Distance (Uncorrected)

B72

B74

. . .

. . . .

Short Field Landing

Distance (Corrected)

B72

B75

. . . . .

. . . .

Short Field Landing

Distance-SEC

(Corrected)

B72

B76

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

. . . .

Short Field Landing

Distance - With Drag

Chute (Uncorrected)

B72

B77

. . . . .

. . . .

Short Field Landing

Distance - With Drag

Chute (Corrected)

B72

B78

. . . . . . .

. . . .

Short Field Landing

Distance - SEC With

Drag Chute (Corrected)

B72

B79

. . .

. . . .

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 pres

sure (antiskid on) in conjunction with twopoint

aerodynamic braking (consistent with maintaining

directional control). When wheel brakes become

effective, the aircraft will automatically rotate to the

threepoint attitude. After the nose tire is on the run

way, 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

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 B71. 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 B72 (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 B72.

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

B72Change 3

SAMPLE PROBLEM (SHEET 1).

A. Altitude

= 2000 feet

B. Temperature

= 40

C. GW

= 28,000 pounds

D. Uncorrected ground

roll distance:

PRI

= 3902 feet

SEC (3902

1.04) = 4058 feet

SAMPLE PROBLEM (SHEET 2).

D. Uncorrected ground

roll distance (SEC)

= 3902 feet

E. RCR

= 16

F. Wind

= 10 knots (headwind)

G. Slope

= 1 percent (uphill)

H. Corrected ground roll

distance

= 3375 feet

I. RCR

= 4

J. Corrected ground roll

distance

= 8000 feet

SAMPLE PROBLEM (SHEET 3).

D. Uncorrected ground

roll distance (SEC)

= 4058 feet

E. RCR

= 16

F. Wind

= 10 knots (headwind)

G. Slope

= 1 percent (uphill)

H. Corrected ground roll

distance

= 3507 feet

I. RCR

= 8

J. Corrected ground roll

distance

= 6031 feet

SAMPLE PROBLEM (SHEET 4).

A. Altitude

= 2000 feet

B. Temperature

= 40

C. GW

= 28,000 pounds

D. Uncorrected ground

roll distance:

PRI

= 2504 feet

SEC (2504

1.02) = 2554 feet

SAMPLE PROBLEM (SHEET 5).

D. Uncorrected ground

roll distance (SEC)

= 2504 feet

E. RCR

= 16

F. Wind

= 10 knots (headwind)

G. Slope

= 1 percent (uphill)

H. Corrected ground roll

distance

= 2107 feet

I. RCR

= 4

J. Corrected ground roll

distance

= 3795 feet

SAMPLE PROBLEM (SHEET 6).

D. Uncorrected ground

roll distance (SEC)

= 2554 feet

E. RCR

= 16

F. Wind

= 10 knots (headwind)

G. Slope

= 1 percent (uphill)

H. Corrected ground roll

distance

= 2158 feet

I. RCR

= 4

J. Corrected ground roll

distance

= 4332 feet

T.O. GR1F16CJ11

B73

1F-16X-1-1-0015B

Landing Speed

DATA BASIS ESTIMATED

CONDITIONS:

CONFIGURATION:

ALL DRAG INDEXES

ALL TEMPERATURES
ALL ALTITUDES

13 DEGREES AOA (INDEXER ON SPEED)

120

140

160

180

200

220

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:

Figure B71.

T.O. GR1F16CJ11

B74Change 3

1F-16CJ-1-1-4043A

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

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 4/5 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 B72.(Sheet 1)

T.O. GR1F16CJ11

Change 3B75

1F-16CJ-1-1-4044A

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

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 B72.(Sheet 2)

T.O. GR1F16CJ11

B76Change 3

1F-16CJ-1-1-4045A

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

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 B72.(Sheet 3)

T.O. GR1F16CJ11

Change 3B77

GR1F-16CJ-1-1-4046A37

1000

2000

3000

4000

5000

6000

7000

GROUND ROLL DIST

ANCE 1000 FEET

TITUDE FEET

NOTE:

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

ALL DRAG INDEXES

SPEEDBRAKES OPEN

DRAG CHUTE DEPLOYED

BELOW 170 KIAS

Short Field Landing Distance With Drag

Chute (Uncorrected)

TOUCHDOWN AT 13 DEGREES AOA

ZERO WIND AND SLOPE

IDLE SELECTED AT TOUCHDOWN

MAX EFFORT BRAKING

DRY CONCRETE RUNWAY

FOR SEC IDLE LANDING, INCREASE UNCORRECTED

GROUND ROLL DISTANCE BY 2 PERCENT. USE SHEET

6 TO DETERMINE CORRECTED GROUND ROLL DISTANCE.

DEPLOYING THE DRAG

DEPLOYING THE DRAG CHUTE AT

AIRSPEEDS GREATER THAN 170

KIAS MAY RESULT IN LOSS OF

THE CHUTE CANOPY.

MLG TIRE LIMIT SPEED

(225 KTS NO WIND)

NLG TIRE LIMIT SPEED

(217 KTS NO WIND)

Figure B72.(Sheet 4)

T.O. GR1F16CJ11

B78Change 3

GR1F-16CJ-1-1-4047A37

DATA BASIS ESTIMATED

CONFIGURATION:

CONDITIONS:

ENGINE F110-GE-129

TOUCHDOWN AT 13 DEGREES AOA

Short Field Landing Distance With Drag

ALL DRAG INDEXES

SPEEDBRAKES OPEN

IDLE SELECTED AT TOUCHDOWN

MAX EFFORT BRAKING

ENTER CHART WITH UNCORRECTED GROUND

ROLL DISTANCE FROM SHEET 4

CORRECTED GROUND ROLL DISTANCE 1000 FEET

UNCORRECTED GROUND ROLL DIST

ANCE 1000 FEET

BASELINE

2
3

WIND

KNOTS

SLOPE

Chute (Corrected)

DRAG CHUTE DEPLOYED

BELOW 170 KIAS

DEPLOYING THE DRAG

CHUTE AT AIRSPEEDS

GREATER THAN 170

KIAS MAY RESULT IN

LOSS OF THE CHUTE

CANOPY.

Figure B72.(Sheet 5)

Content .. 70 71 72 73 ..

F16C/D. FLIGHT MANUAL (2002) - page 72

F16C/D. FLIGHT MANUAL (2002) - page 72